# AD 96-01-02: Aft Mount Beam Assembly - Type: Airworthiness directive - Status: Current - Products: Boeing MD-11 and MD-11F - Effective: February 20, 1996 - Published: January 19, 1996, 61 FR 1278–1279 - Issued as: Final rule - Supersedes: [AD 95-11-13](https://openairdocs.org/ad/95-11-13) - Superseded by: Nothing supersedes this AD - Product type: Aircraft, Large airplane - Amendment: 39-9478 - Docket: 95-NM-97-AD - Registered aircraft: 108 may be affected, by airframe or engine model (OpenAirDocs) - Official PDF: https://openairdocs.org/files/sha256/d8/4a/d84a15074673d10e64193c85afe4448877090435663471ee47a8534e01ff3b79 (from https://www.govinfo.gov/content/pkg/FR-1996-01-19/pdf/96-533.pdf) - Federal Register: https://www.federalregister.gov/documents/1996/01/19/96-533/airworthiness-directives-mcdonnell-douglas-model-md-11-series-airplanes-equipped-with-pratt-and - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/D40C6DF0EA4F730D86256A080067130A.0001 - DRS record last changed: May 30, 2024 - Page: https://openairdocs.org/ad/96-01-02 ## Summary This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a visual inspection to detect cracks or discrepancies in the aft mount beam assembly of the engines; and replacement of the cracked or discrepant aft mount beam assembly with a new assembly, or a previously inspected and re-identified assembly. That amendment was prompted by reports of cracking in a certain aft mount beam assembly. This new amendment requires additional inspections to detect cracks or discrepancies in the subject area, and various follow-on actions. The actions specified by this amendment are intended to prevent cracks in the aft mount beam assembly of the engines, which could result in loss of the capability of the aft mount beam assembly to support engine loads, and possible separation of the engine from the airplane. ## The airworthiness directive 96-01-02 MCDONNELL DOUGLAS: Amendment 39-9478. Docket 95-NM-97-AD. Supersedes AD 95-11-13, Amendment 39-9246. Applicability: Model MD-11 series airplanes, equipped with Pratt & Whitney Model PW4460 and PW4462 engines; as listed in McDonnell Douglas Alert Service Bulletin MD11-71A073, Revision 1, dated May 16, 1995; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (e) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent loss of the capability of the aft mount beam assembly to support engine loads, and possible separation of the engine from the airplane, accomplish the following: (a) Within 60 days after June 16, 1995 (the effective date of AD 95-11-13, amendment 39-9246), perform a visual inspection to detect cracks or discrepancies in the aft mount beam assembly, part number (P/N) 221-0261-501, of engine numbers 1, 2, and 3, in accordance with McDonnell Douglas Alert Service Bulletin MD11-71A073, Revision 1, dated May 16, 1995, or Revision 2, dated October 10, 1995. (1) If no cracks or discrepancies are detected, no further action is required by paragraph (a) of this AD. (2) If any crack or discrepancy is detected, prior to further flight, replace the cracked or discrepant aft mount beam assembly with a new assembly having P/N 221-0261-503, or an assembly having P/N 221-0261-501 that has been previously inspected and re-identified, in accordance with paragraph 3.B., Phase 2, of the Accomplishment Instructions of the alert service bulletin. Replacement shall be accomplished in accordance with the procedures specified in either alert service bulletin. (b) Within 4,000 flight cycles after accomplishing any inspection required by this AD, perform etch fluorescent penetrant and eddy current inspections to detect cracks or discrepancies in the aft mount beam assembly, P/N 221-0261-501, of engine numbers 1, 2, and 3, in accordance with McDonnell Douglas Alert Service Bulletin MD11-71A073, Revision 1, dated May 16, 1995, or Revision 2, dated October 10, 1995. (1) If no crack or discrepancy is detected, prior to further flight, re-identify and install the aft mount beam assembly in accordance with the alert service bulletin. (2) If any crack or discrepancy is detected, prior to further flight, replace the cracked or discrepant aft mount beam assembly with a new assembly having P/N 221-0261-503, or an assembly having P/N 221-0261-501 that has been previously inspected and re-identified, in accordance with paragraph 3.B., Phase 2, of the Accomplishment Instructions of the alert service bulletin. Replacement shall be accomplished in accordance with the procedures specified in the alert service bulletin. (c) Within 10 days after accomplishing any inspection required by this AD, report inspection results, positive or negative, to the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California 90712; fax (310) 627-5210. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (d) As of June 16, 1995 (the effective date of AD 95-11-13, amendment 39-9246), no person shall install an aft mount beam assembly, P/N 221-0261-501, on any airplane, unless it has been previously inspected and re-identified in accordance with paragraph 3.B., Phase 2, of the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin MD11-71A073, Revision 1, dated May 16, 1995, or Revision 2, dated October 10, 1995. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The inspections and replacement shall be done in accordance with McDonnell Douglas Alert Service Bulletin MD11-71A073, Revision 1, dated May 16, 1995, or McDonnell Douglas Alert Service Bulletin MD11-71A073, Revision 2, dated October 10, 1995. The incorporation by reference of McDonnell Douglas Alert Service Bulletin MD11-71A073, Revision 2, dated October 10, 1995, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. The incorporation by reference of McDonnell DouglasAlert Service Bulletin MD11-71A073, Revision 1, dated May 16, 1995, was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of as of June 16, 1995 (60 FR 28527, June 1, 1995). Copies may be obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Technical Publications Business Administration, Department C1-L51 (2-60). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on February 20, 1996. ## Rule preamble ### Supplementary information A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 95-11-13, amendment 39-9246 (60 FR 28527, June 1, 1995), which is applicable to certain McDonnell Douglas Model MD-11 series airplanes, was published in the Federal Register on June 26, 1995 (60 FR 32926). (A correction of that rule was published in the Federal Register on June 15, 1995 (60 FR 31387).) The action proposed to continue to require the one-time visual inspection to detect cracks or discrepancies in the aft mount beam assembly of the engines; and replacement of the aft mount beam assembly, if necessary. It also proposed to add etch fluorescent penetrant inspections as well as eddy current inspections to detect cracks or discrepancies in the aft mount beam assembly of the engines; and to require various follow-on actions. Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received. One commenter supports the proposed rule. Two commenters request that the proposed rule be revised to cite the latest revision of McDonnell Douglas Alert Service Bulletin MD11-71A073 as an additional source of service information. The FAA concurs. Since the issuance of the proposed rule, the FAA has reviewed and approved Revision 2 of McDonnell Douglas Alert Service Bulletin MD11-71A073, dated October 10, 1995. Except for minor edits, this revised service bulletin is essentially identical to Revision 1 and does not entail any additional work on the part of affected operators. The FAA has revised the final rule to reference Revision 2 of the service bulletin as an additional source of service information. After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the changes previously described. The FAA hasdetermined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. There are approximately 57 Model MD-11 series airplanes equipped with Pratt & Whitney Model PW4460 and PW4462 engines of the affected design in the worldwide fleet. The FAA estimates that 17 airplanes of U.S. registry will be affected by this AD. The visual inspection that was previously required by AD 95-11-13, and retained in this AD, takes approximately 2 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the visual inspection requirement on U.S. operators is estimated to be $2,040, or $120 per airplane. The FAA estimates that all affected U.S. operators have already accomplished this action; therefore, any future cost impact of this requirement is expected to be minimal. The fluorescent penetrant and eddy current inspections that are required by this new AD will take approximately 15 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the fluorescent penetrant and eddy current inspection requirements on U.S. operators is estimated to be $15,300, or $900 per airplane, per inspection cycle. This cost impact figure is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasonsdiscussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES1. The authority citation for part 39 continues to read as follows: Authority: 49 USC 106(g), 40101, 40113, 44701. § 39.13 - (Amended) 2. Section 39.13 is amended by removing amendment 39-9246 (60 FR 31387, June 15, 1995), and by adding a new airworthiness directive (AD), amendment 39-9478, to read as follows: ## Affected data sheets (1) (OpenAirDocs) The type certificate data sheets whose models the AD names. - [TCDS A22WE](https://openairdocs.org/tcds/A22WE): The Boeing Company; names 2 of 11 models: MD-11, MD-11F ## Registered aircraft it may apply to (OpenAirDocs) Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment. - Aircraft: 108 (108 by airframe model, 0 by engine model) - Makers: Mcdonnell Douglas 104, Boeing 4 Models with the most aircraft: - [Mcdonnell Douglas MD-11F](https://openairdocs.org/model/mcdonnell-douglas-md-11f): 100 aircraft (airframe model) - [Mcdonnell Douglas MD-11](https://openairdocs.org/model/mcdonnell-douglas-md-11): 4 aircraft (airframe model) - [Boeing MD-11F](https://openairdocs.org/model/boeing-md-11f): 4 aircraft (airframe model) All 3 models: https://openairdocs.org/ad/96-01-02/models.md Every aircraft: https://openairdocs.org/ad/96-01-02/aircraft.md ## Related documents - [AD 95-11-13](https://openairdocs.org/ad/95-11-13) (historical): Aft Mount Beam Assembly · McDonnell Douglas MD-11 Series (all). Effective Jun 16, 1995. Replaced by this AD - [Proposed rule 95-NM-97-AD](https://openairdocs.org/proposed/95-NM-97-AD): Notice of proposed rulemaking (NPRM), published Jun 26, 1995 Its text cites no advisory circulars or STCs. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.