- Effective
- July 28, 2014
- Published
- June 23, 2014 · 79 FR 35479–35481
- Issued
- June 4, 2014
- Model
- 727-100 Series
- Data sheet
- TCDSA3WE
- Product
- Aircraft · Large airplane
- ATA chapter
- 53 · Fuselage
- Amendment
- 39-17871
- Docket
- FAA-2014-0141
- Project
- 2013-NM-024-AD
- Issued as
- Final rule
Unofficial copy from the Federal Register XML, document 2014-13830. Only the govinfo PDF is the legal edition. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 233 KB | 6c54d23d…48b57a4 | 2014-13830.pdf on govinfo.gov |
| Federal Register XML | 20 KB | 22c95747…f946a72 | 2014-13830.xml on federalregister.gov |
| FAA DRS HTML attachment | 60 KB | 4b20d5f0…6af2419 | FAA DRS (API key needed) |
| FAA DRS PDF | 60 KB | d4f89867…c55fa08 | FAA DRS (API key needed) |
On this page
Summary
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727-100 series airplanes. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. For certain airplanes, this AD requires repetitive inspections for cracking in stringers or frames until modification, and repair if necessary. We are issuing this AD to detect and correct cracking in stringers or frames originating at or near stringer-to-frame attachment fastener holes, which could result in reduced structural integrity of the airplane, and decompression of the cabin.
The airworthiness directive
2014-12-10 The Boeing Company: Amendment 39-17871; Docket No. FAA-2014-0141; Directorate Identifier 2013-NM-024-AD.
(a) Effective Date
PDF page 2This AD is effective July 28, 2014.
(b) Affected ADs
PDF page 2None.
(c) Applicability
PDF page 2This AD applies to The Boeing Company Model 727-100 series airplanes, certificated in any category, as identified in Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991, unless previously modified using the service information specified in paragraphs (c)(1), (c)(2), or (c)(3) of this AD.
(1) Boeing Service Bulletin 727-53-0041, Revision 4, dated July 27, 1973.
(2) Boeing Service Bulletin 727-53-0041, Revision 5, dated January 25, 1990.
(3) Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991.
Note 1 to paragraph (c) of this AD:
Boeing Service Bulletin 727-53-0041, Revision 4, dated July 27, 1973, is specified in Boeing Document D6-54860 “Aging Airplane Service Bulletin Structural Modification Program—Model 727,” Revision C, dated December 11, 1989, as mandated by AD 90-06-09, Amendment 39-6488 (55 FR 8370, March 7, 1990).
(d) Subject
PDF page 2Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
PDF page 2This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. We are issuing this AD to detect and correct cracking in stringers or frames originating at or near stringer-to-frame attachment fastener holes, which could result in reduced structural integrity of the airplane, and decompression of the cabin.
(f) Compliance
PDF page 2Comply with this AD within the compliance times specified, unless already done.
(g) Inspections
PDF page 2Before the accumulation of 16,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later, do a high frequency eddy current inspection and a general visual inspection for cracking in stringers and frames originating at or near stringer-to-frame attachment fastener holes, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991. Repeat the inspections thereafter at intervals not to exceed 6,000 flight cycles until the modification specified by paragraph (h) of this AD is accomplished. If any crack is found during any inspection required by this paragraph: Before further flight, repair or modify the affected stringer-to-frame attachment locations, in accordance with Part V, “Repair Data,” of the Accomplishment Instructions of Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991.
(h) Modification
PDF page 2Modifying the affected stringer-to-frame attachment locations, in accordance with Part IV, “Preventive Modification Data,” of the Accomplishment Instructions of Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991, terminates the repetitive inspections required by paragraph (g) of this AD.
(i) Alternative Methods of Compliance (AMOCs)
PDF page 2(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOC-REQUESTS@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office.
(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.
(j) Related Information
PDF page 3For more information about this AD, contact Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov.
(k) Material Incorporated by Reference
PDF page 3(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991.
(ii) Reserved.
(3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221.
(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
DatesPage 1
This AD is effective July 28, 2014.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 28, 2014.
AddressesPage 1
For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221.
For further information contactPage 1
Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov.
DiscussionPage 1
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 727-100 series airplanes. The NPRM published in the Federal Register on March 12, 2014 (79 FR 13931). The NPRM proposed actions intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. For certain airplanes, the NPRM proposed to require repetitive inspections for cracking in stringers or frames until modification, and repair if necessary. We are issuing this AD to detect and correct cracking in stringers or frames originating at or near stringer-to-frame attachment fastener holes, which could result in reduced structural integrity of the airplane, and decompression of the cabin.
CommentsPage 1
We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 13931, March 12, 2014) or on the determination of the cost to the public.
ConclusionPage 1
We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:
• Are consistent with the intent that was proposed in the NPRM (79 FR 13931, March 12, 2014) for correcting the unsafe condition; and
• Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 13931, March 12, 2014).
Costs of CompliancePage 1
We estimate that this AD affects 2 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
| Action | Labor cost | Parts cost | Cost per product | Cost on U.S. operators |
|---|---|---|---|---|
| Inspections | 60 work-hours × $85 per hour = $5,100 per inspection cycle | $0 | $5,100 per inspection cycle | $10,200 per inspection cycle. |
We estimate the following costs to do any necessary modifications that would be required based on the results of the inspections. We have no way of determining the number of aircraft that might need these modifications:
| Action | Labor cost | Parts cost | Cost per product |
|---|---|---|---|
| Modification | 600 work-hours × $85 per hour = $51,000 per inspection cycle | Up to $11,481 | Up to $62,481 per modification. |
Authority for This RulemakingPage 2
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory findingsPage 2
This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect 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.
For the reasons discussed above, I certify that this AD:
(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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
Adoption of the AmendmentPage 2
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
Adoption of the amendmentPage 2
1. The authority citation for part 39 continues to read as follows:
2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.