- Effective
- July 22, 2011
- Published
- June 17, 2011 · 76 FR 35342–35344
- Issued
- May 31, 2011
- Model
- MD-90-30
- Data sheet
- TCDSA6WE
- Registered aircraft
- 5 matched by model
- Product
- Aircraft · Large airplane
- ATA chapter
- 55 · Stabilizers
- Amendment
- 39-16719
- Docket
- FAA-2011-0218
- Project
- 2010-NM-164-AD
- Issued as
- Final rule
Unofficial copy from the Federal Register XML, document 2011-14339. 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 | 158 KB | 8e1f02dc…b42739e | 2011-14339.pdf on govinfo.gov |
| Federal Register XML | 21 KB | 7a65096b…318bc9e | 2011-14339.xml on federalregister.gov |
| FAA DRS HTML attachment | 63 KB | 85142ad1…c7be514 | FAA DRS (API key needed) |
| FAA DRS PDF | 44 KB | 221626f8…0daa18e | FAA DRS (API key needed) |
On this page
Summary
We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires a detailed inspection to detect distress and existing repairs to the leading edge structure of the vertical stabilizer at the splice at Station Zfs=52.267; repetitive inspections for cracking in the front spar cap forward flanges of the vertical stabilizer, and either the aft flanges or side skins; repetitive inspections for loose and missing fasteners; and related investigative and corrective actions if necessary. This AD was prompted by reports of cracked vertical stabilizer skin, a severed front spar cap, elongated fastener holes at the leading edge of the vertical stabilizer, and cracked front spar web and front spar cap bolt holes in the vertical stabilizer. We are issuing this AD to detect and correct such cracking damage, which could result in the structure being unable to support limit load, and could lead to the loss of the vertical stabilizer.
The airworthiness directive
2011-12-12 The Boeing Company: Amendment 39-16719; Docket No. FAA-2011-0218; Directorate Identifier 2010-NM-164-AD.
(a) Effective Date
PDF page 2(a) This AD is effective July 22, 2011.
(b) Affected ADs
PDF page 2(b) None.
(c) Applicability
PDF page 2(c) This AD applies to The Boeing Company Model MD-90-30 airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin MD90-55A014, dated June 24, 2010.
(d) Subject
PDF page 2(d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 55: Stabilizers.
(e) Unsafe Condition
PDF page 2(e) This AD was prompted by reports of cracked vertical stabilizer skin, a severed front spar cap, elongated fastener holes at the leading edge of the vertical stabilizer, and cracked front spar web and front spar cap bolt holes in the vertical stabilizer. We are issuing this AD to detect and correct such cracking damage, which could result in the structure being unable to support limit load, and could lead to the loss of the vertical stabilizer.
(f) Compliance
PDF page 2(f) Comply with this AD within the compliance times specified, unless already done.
(g) Inspections for Distress/Repairs
PDF page 2(g) Within 4,100 flight cycles after the effective date of this AD, do a detailed inspection for distress in and existing repairs to the leading edge structure of the vertical stabilizer at the splice at Station Zfs=52.267, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90-55A014, dated June 24, 2010.
(h) Repetitive Inspections for Cracks, and Related Investigative and Corrective Actions
PDF page 2(h) Before further flight after doing the inspection required by paragraph (g) of this AD, inspect for cracks of the left and right vertical stabilizer front spar cap, in accordance with either Option 1 or Option 2 as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin MD90-55A014, dated June 24, 2010. If any crack is found, before further flight, evaluate and verify to confirm all crack indications, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90-55A014, dated June 24, 2010.
(1) If any cracking is confirmed, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD.
(2) If no cracking is confirmed, repeat the inspection thereafter at intervals not to exceed the applicable interval specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD.
(i) If the most recent inspection was done using Option 1, the next inspection must be done within 4,400 flight cycles.
(ii) If the most recent inspection was done using Option 2, the next inspection must be done within 3,000 flight cycles.
(i) Leading Edge Repair
PDF page 2(i) If leading edge distress is found during the detailed inspection required by paragraph (g) of this AD, before further flight and after accomplishing the inspection required by paragraph (h) of this AD, repair the leading edge, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90-55A014, dated June 24, 2010.
(j) Inspection for Loose/Missing Fasteners
PDF page 2(j) For airplanes on which no cracking is confirmed during the initial inspection required by paragraph (h) of this AD: At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD, do a detailed inspection for indications of loose and missing fasteners, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90-55A014, dated June 24, 2010. If any loose or missing fastener is found, before further flight, repair the leading edge, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90-55A014, dated June 24, 2010.
(1) If the inspection required by paragraph (h) was done using Option 1, do the inspection required by paragraph (j) of this AD within 4,400 flight cycles after accomplishing the inspection required by paragraph (h) of this AD.
(2) If inspection required by paragraph (h) was done using Option 2, do the inspection required by paragraph (j) of this AD within 3,000 flight cycles after accomplishing the inspection required by paragraph (h) of this AD.
(k) For airplanes on which no cracking is confirmed during the most recent inspection required by paragraph (h) of this AD: Repeat the inspection for loose and missing fasteners required by paragraph (j) of this AD thereafter at intervals not to exceed the applicable time specified in paragraph (k)(1) or (k)(2) of this AD.
(1) If the most recent inspection required by paragraph (h) was done using Option 1, the next inspection required by paragraph (j) of this AD must be done within 4,400 flight cycles after accomplishing the most recent inspection required by paragraph (j) of this AD.
(2) If the most recent inspection required by paragraph (h) was done using Option 2, the next inspection required by paragraph (j) of this AD must be done within 3,000 flight cycles after the most recent inspection required by paragraph (j) of this AD.
(l) Alternative Methods of Compliance (AMOCs)
PDF page 3(l)(1) The Manager, Los Angeles Aircraft Certification Office, 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 the Related Information section of this AD.
(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.
(m) Related Information
PDF page 3(m) For more information about this AD, contact Roger Durbin, Aerospace Engineer, Airframe Branch, ANM-120L, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5233; fax: 562-627-5210; e-mail: Roger.Durbin@faa.gov.
(n) Material Incorporated by Reference
PDF page 3(n) You must use of Boeing Alert Service Bulletin MD90-55A014, dated June 24, 2010, to do the actions required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-0001; phone: 206-544-5000, extension 2; fax: 206-766-5683; e-mail: dse.boecom@boeing.com; Internet: https://www.myboeingfleet.com.
(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221.
(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
DatesPage 1
This AD is effective July 22, 2011.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 22, 2011.
AddressesPage 1
For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-0001; phone: 206-544-5000, extension 2; fax: 206-766-5683; e-mail: dse.boecom@boeing.com; Internet: https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221.
For further information contactPage 1
Roger Durbin, Aerospace Engineer, Airframe Branch, ANM-120L, Los Angeles ACO, 3960 Paramount Blvd, Lakewood, CA 90712-4137; phone: 562-627-5233; fax: 562-627-5210; e-mail: Roger.Durbin@faa.gov.
DiscussionPage 1
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That NPRM published in the Federal Register on March 14, 2011 (76 FR 13546). That NPRM proposed to require a detailed inspection to detect distress in, and existing repairs to, the leading edge structure of the vertical stabilizer at the splice at Station Zfs=52.267, and corrective action if necessary.
CommentsPage 1
We gave the public the opportunity to participate in developing this AD. We have considered the comment received. The Boeing Company supports the NPRM.
ConclusionPage 1
We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD as proposed.
Costs of CompliancePage 1
We estimate that this AD affects 19 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 |
|---|---|---|---|---|
| Inspection for existing repairs, distress | 10 work-hours × $85 per hour = $850 | $0 | $850 | $16,150. |
| Repetitive inspections for cracking and loose and missing fasteners | 7 work-hours × $85 per hour = $595 per inspection cycle | 0 | $595 per inspection cycle | $11,305 per inspection cycle. |
We have received no definitive data that would enable us to provide cost estimates for the on-condition action specified in this AD.
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.
Registered aircraft · 5
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1995 | 1 |
|---|---|
| 1996 | 2 |
| 1998 | 1 |
| 1999 | 1 |