82 FR 24468 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 102 (May 30, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 102 (May 30, 2017)
| Page Range | 24468-24472 | |
| FR Document | 2017-10288 |
[Federal Register Volume 82, Number 102 (Tuesday, May 30, 2017)] [Rules and Regulations] [Pages 24468-24472] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10288] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6667; Directorate Identifier 2015-NM-125-AD; Amendment 39-18882; AD 2017-10-08] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2009-21-01 for certain The Boeing Company Model 737-300 and 737-400 series airplanes. AD 2009-21-01 required repetitive inspections to detect cracking of the aft fuselage skin, and related investigative and corrective actions if necessary. This new AD adds certain inspections, repairs, replacement, related investigative and corrective actions if necessary; and removes certain airplanes from the applicability. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft fuselage skin is subject to widespread fatigue damage (WFD), and by reports of aft fuselage cracking. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 5, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 5, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 6667. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 6667; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2009-21-01, Amendment 39-16038 (74 FR 52395, October 13, 2009) (``AD 2009-21-01''). AD 2009-21-01 applied to certain the Boeing Company Model 737-300 and 737-400 series airplanes. The NPRM published in the Federal Register on May 13, 2016 (81 FR 29802). The NPRM was prompted by an evaluation by the DAH indicating that the aft fuselage skin is subject to WFD, and by reports of aft fuselage cracking. The NPRM proposed to continue to require repetitive inspections to detect cracking of the aft fuselage skin, and related investigative and corrective actions if necessary. The NPRM also proposed to add new aft fuselage skin inspections for cracking, inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers, permanent repairs of time-limited repairs, related investigative and corrective actions if necessary, and skin panel replacement. The NPRM also proposed to remove Model 737-400 series airplanes from the applicability. We are issuing this AD to detect and correct cracking in the aft fuselage skin along the longitudinal edges of the chem-milled pockets in the bonded skin doubler, which could result in possible rapid decompression and reduced structural integrity of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Revise the Precipitating Event Statement Boeing requested that we revise the precipitating event statement by including that there have been reports of aft fuselage cracking. Boeing stated that this revision would be consistent with wording of other related rulemaking. We agree with Boeing's request because it provides additional clarity to the precipitating event statement. We have revised the SUMMARY and Discussion sections, and paragraph (e) of this AD accordingly. [[Page 24469]] Request To Require Reinstalling Lap Joint Modification Jet2.com Limited (Jet2) requested that we revise the NPRM to require reinstalling the lap joint modification previously installed in accordance with AD 2015-21-06, Amendment 39-18298 (80 FR 69839, November 12, 2015) (``AD 2015-21-06''), which requires the S-14 lap joint to be trimmed out prior to 50,000 total flight cycles. Jet2 stated that Boeing Special Attention Service Bulletin 737-53-1168, Revision 4, dated June 3, 2015 (``SASB 737-53-1168, Revision 4'') specifies reinstalling the lap joint modification. We do not agree with the commenter's request. The modification required in AD 2015-21-06 consists of trimming out the lap splice, such that if this modification were installed, it would be impossible to install a new skin without reinstalling the lap modification. If the instructions in SASB 737-53-1168, Revision 4, to reinstall the lap splice modification were accidently overlooked, it would become clear to the installer that the reinstallation would be required. We have not changed this AD in this regard. Request To Address Certain Repairs Boeing requested that we add a paragraph to the proposed AD to address repairs that are installed on the airplane for reasons other than chem-mill cracking. Boeing submitted suggested language and pointed out that the additional language is similar to that in other rulemaking. We disagree with Boeing's request. Part 1 of the Accomplishment Instructions of SASB 737-53-1168, Revision 4, does not make a distinction regarding why an existing repair was installed. Therefore, repairs installed for damage other than a chem-mill crack are already addressed. We have not changed this AD in this regard. Request To Revise Proposed Compliance Time Boeing requested that we revise paragraph (h)(4) of the proposed AD to do the actions at an initial compliance time obtained through the alternative method of compliance (AMOC) process specified in paragraph (n)(1) of the proposed AD. Boeing stated that the repetitive inspections would still be done at the times specified in the service information. Boeing also requested that we include in the paragraph revision the terminating action of skin panel replacement at the time approved through an AMOC. Boeing stated that its request would provide a reset on the compliance times if the skin panel was replaced prior to 53,000 total airplane cycles. Boeing explained that its authorized representative under the Boeing Commercial Airplanes Organization Designation Authorization (ODA) cannot approve extensions to the compliance times. We partially agree with Boeing's request. We agree that, for airplanes with skin panels replaced prior to 53,000 total flight cycles, in order to reset the inspection threshold on the replaced skin panels, approval must come from the FAA. Under the provisions of paragraph (n) of this AD, we may consider requests for a reset of the compliance times if the skin panel was replaced prior to 53,000 total airplane cycles if data are submitted to substantiate that such an adjustment would provide an acceptable level of safety. We have not changed this AD in this regard. Request To Specify the Service Information Accomplishment Instructions Part Numbers Boeing requested that we add the specific part of the accomplishment instructions in paragraphs (i)(1)(ii), (i)(2)(ii), and (j) of the proposed AD. Boeing stated that paragraph (g) of the proposed AD specifies the specific part number, and that this change would make these paragraphs consistent with the wording in paragraph (g) of the proposed AD. We agree with Boeing's request. We agree that specifying the specific part of the Accomplishment Instructions of SASB 737-53-1168, Revision 4, will add clarity to the AD. We have revised paragraphs (i)(1)(ii), (i)(2)(ii), and (j) of this AD accordingly. Request To Revise Flight Cycle Limit for Replacement Kit Skin Panels Boeing requested that we revise paragraph (l) of the proposed AD to specify that skin panel replacements using the kit identified in SASB 737-53-1168, Revision 4, do not have the lower flight cycle limit restriction that the production skin panel replacements have. We agree with Boeing's request because the skin panel replacements using the kit identified in SASB 737-53-1168, Revision 4, is an improved design compared to the production skin panels, and therefore, do not need the lower flight cycle limit restriction. We have added paragraph (l)(3) to this AD, which states, in part, that if the skin panel is replaced with a kit skin panel as specified in SASB 737-53- 1168, Revision 4, the 53,000 total flight cycle limit does not apply. Request To Remove Flight-Cycle Restriction for Certain Actions Boeing requested that we revise paragraphs (m)(2), (m)(3), and (n)(5) of the proposed AD to remove the flight cycle restriction for certain previously accomplished actions using certain service information. Boeing stated that the only skin panel replacements specified in previous revisions of SASB 737-53-1168 are those using the kit panels, and that those panels do not have the flight-cycle limit specified in paragraphs (m)(2), (m)(3), and (n)(5) of the proposed AD. We agree with the commenter's request because the skin panel replacements using the kit identified in SASB 737-53-1168, Revision 4, are an improved design compared to the production skin panels, and therefore, do not need the lower flight cycle limit restriction. We have revised paragraphs (m)(2), (m)(3), and (n)(5) of this AD accordingly. Request To Specify Terminating Action Qantas Airways Limited (Qantas) requested that we revise paragraphs (g) and (l) of the proposed AD to specify terminating action. Qantas pointed out that replacing the skin panels with kit panels instead of production panels, as specified in SASB 737-53-1168, terminates the repetitive inspections identified in paragraphs (g), (i), and (j) of the proposed AD. Additionally, Qantas pointed out that replacement with kit skin panels using any revision of SASB 737-53-1168 before the effective date of the AD should also terminate the repetitive inspections identified in paragraphs (g), (i), and (j) of the proposed AD. We agree with the commenter's request because the skin panel replacements using the kit identified in SASB 737-53-1168, Revision 4, are an improved design compared to the production skin panels and therefore, should terminate the repetitive inspections. We have revised paragraphs (m)(2), (m)(3), and (n)(5) of this AD accordingly. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing Supplemental Type Certificate (STC) ST01219SE does not affect the actions specified in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1) of this AD and added paragraph (c)(2) to this AD to state that installation of STC ST01219SE does not affect the ability to [[Page 24470]] accomplish the actions required by this final rule. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' AMOC approval request is not necessary to comply with the requirements of 14 CFR 39.17. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously, and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed SASB 737-53-1168, Revision 4. The service information describes procedures for doing inspections of the fuselage skin, repairs, and skin panel replacement. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 168 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- Inspections.................. Up to 1,791 work- $0 Up to $152,235. Up to $25,575,480. hours x $85 per hour = $152,235. Skin replacement............. 624 work-hours x $85 98,275 $151,315....... $25,420,920. per hour = $53,040. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs 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 repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Time-limited repair............. 24 work-hours x $85 per (\1\) $2,040 per repair. hour = $2,040 per repair. Permanent repair................ Up to 43 work[dash]hours (\1\) Up to $3,655 per repair. x $85 per hour = $3,655 per repair. ---------------------------------------------------------------------------------------------------------------- \1\ We have received no definitive data that would enable us to provide the part cost estimates for the on- condition actions specified in this AD. We estimate the following costs to do any necessary post-repair inspections that would be required. We have no way of determining the number of aircraft that might need these inspections: Post-Repair Inspection Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Post-repair inspection.......... Up to 7 work[dash]hours $0 Up to $595. x $85 per hour = $595. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking 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 Findings We have determined that 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, [[Page 24471]] the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2009-21-01, Amendment 39-16038 (74 FR 52395, October 13, 2009), and adding the following new AD: 2017-10-08 The Boeing Company: Amendment 39-18882; Docket No. FAA- 2016-6667; Directorate Identifier 2015-NM-125-AD. (a) Effective Date This AD is effective July 5, 2017. (b) Affected ADs This AD replaces AD 2009-21-01, Amendment 39-16038 (74 FR 52395, October 13, 2009) (``AD 2009-21-01''). (c) Applicability (1) This AD applies to The Boeing Company Model 737-300 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 737-53-1168, Revision 4, dated June 3, 2015 (``SASB 737-53-1168, Revision 4''). (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft fuselage skin is subject to widespread fatigue damage (WFD), and reports of aft fuselage cracking. We are issuing this AD to detect and correct cracking in the aft fuselage skin along the longitudinal edges of the chem- milled pockets in the bonded skin doubler, which could result in possible rapid decompression and reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections, Related Investigative and Corrective Actions At the applicable times specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1168, Revision 4, except as required by paragraphs (h)(1) and (h)(2) of this AD: Do the applicable inspections to detect cracks in the aft fuselage skin panels, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of SASB 737-53-1168, Revision 4, except as required by paragraphs (h)(3) and (h)(4) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable intervals specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' of SASB 737-53- 1168, Revision 4. Accomplishment of a repair in accordance with ``Part 4: Repair'' of the Accomplishment Instructions of SASB 737- 53-1168, Revision 4, except as required by paragraph (h)(3) of this AD, is terminating action for the repetitive inspections required by this paragraph at the repaired locations only. (h) Exceptions to SASB 737-53-1168, Revision 4 (1) Where SASB 737-53-1168, Revision 4, specifies compliance times ``after the Revision 4 date of this service bulletin,'' this AD requires compliance within the specified compliance times after the effective date of this AD. (2) The Condition column of paragraph 1.E., ``Compliance,'' of SASB 737-53-1168, Revision 4, refers to airplanes in certain configurations as of the ``issue date of Revision 4 of this service bulletin.'' However, this AD applies to airplanes in the specified configurations ``as of the effective date of this AD.'' (3) Where SASB 737-53-1168, Revision 4, specifies contacting Boeing for repair instructions or work instructions, before further flight, repair or perform the work instructions using a method approved in accordance with the procedures specified in paragraph (n) of this AD, except as required by paragraph (h)(4) of this AD. (4) For airplanes on which an operator has a record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles: At the applicable time for the next inspection as specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1168, Revision 4, except as provided by paragraph (h)(1) and (h)(2) of this AD, perform inspections and applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (i) Actions for Airplanes With a Time-Limited Repair Installed (1) For airplanes with a time-limited repair installed, as specified in Boeing Service Bulletin 737-53-1168, Revision 3, dated November 28, 2006: At the applicable times specified in table 3 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1168, Revision 4, except as provided by paragraphs (h)(1) and (h)(2) of this AD, do the actions specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (i) Do the applicable inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of SASB 737-53-1168, Revision 4, except as required by paragraph (h)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable intervals specified in SASB 737-53-1168, Revision 4. (ii) Make the time-limited repair permanent, and do all applicable related investigative and corrective actions, in accordance with Part 6 of the Accomplishment Instructions of SASB 737-53-1168, Revision 4, except as required by paragraph (h)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Accomplishing the permanent repair required by this paragraph terminates the inspections required by paragraph (i)(1)(i) of this AD for the permanently repaired area only. (2) For airplanes with a time-limited repair installed, as specified in SASB 737-53-1168, Revision 4: At the applicable times specified in table 4 of paragraph 1.E., ``Compliance,'' of SASB 737- 53-1168, Revision 4, do the actions specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD. (i) Do the applicable inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of SASB 737-53-1168, Revision 4, except as required by paragraph (h)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable intervals specified in table 4 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1168, Revision 4. (ii) Make the time-limited repair permanent, and do all applicable related investigative and corrective actions, in accordance with Part 6 of the Accomplishment Instructions of SASB 737-53-1168, Revision 4, except as required by paragraph (h)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Accomplishing the permanent repair required by this paragraph terminates the inspections required by paragraph (i)(2)(i) of this AD for the permanently repaired area only. (j) Modification of Certain Permanent Repairs For airplanes with an existing time-limited repair that was made permanent, as specified in Boeing Service Bulletin 737-53-1168, Revision 3, dated November 28, 2006: At the applicable times specified in table 5 of paragraph 1.E., ``Compliance,'' of SASB 737- 53-1168, Revision 4, except as provided by paragraphs (h)(1) of this AD, modify the existing permanent repair, and do all applicable related investigative and corrective actions, in accordance with Part 6 of the Accomplishment Instructions of SASB 737-53-1168, Revision 4, except as required [[Page 24472]] by paragraph (h)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. (k) Post-Repair Inspections Table 6 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1168, Revision 4, specifies post-repair airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the repaired locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an AMOC. (l) Skin Panel Replacement At the later of the times specified in paragraphs (l)(1), (1)(2), and (l)(3) of this AD: Replace the applicable skin panels, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of SASB 737-53- 1168, Revision 4. Do all applicable related investigative and corrective actions before further flight. Doing the skin panel replacement required by this paragraph terminates the inspection requirements of paragraphs (g), (i), and (j) of this AD for that skin panel only, provided the skin panel replacement was done with a production skin panel after 53,000 total flight cycles. (1) Before 60,000 total flight cycles, but not before 53,000 total flight cycles. (2) Within 6,000 flight cycles after the effective date of this AD, but not before 53,000 total flight cycles. (3) If the skin panel is replaced with a production skin panel, not before 53,000 total flight cycles. If the skin panel is replaced with a kit skin panel as specified in SASB 737-53-1168, Revision 4, the 53,000 total flight cycle limit does not apply. (m) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 737-53-1168, Revision 3, dated November 28, 2006, except as required by paragraph (h)(4) of this AD. Boeing Service Bulletin 737-53-1168, Revision 3, dated November 28, 2006, was incorporated by reference in AD 2009- 21-01. (2) This paragraph provides credit for the actions required by paragraph (l) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 737-53-1168, Revision 3, dated November 28, 2006, except as required by paragraph (h)(4) of this AD. Boeing Service Bulletin 737-53-1168, Revision 3, dated November 28, 2006, was incorporated by reference in AD 2009- 21-01. (3) This paragraph provides credit for the actions required by paragraph (l) of this AD, if those actions were performed before November 17, 2009 (the effective date of AD 2009-21-01), using any service information specified in paragraphs (m)(3)(i), (m)(3)(ii), and (m)(3)(iii) of this AD, provided the replacement is made with a kit skin panel, except as required by paragraph (h)(4) of this AD. The service information specified in paragraphs (m)(3)(i), (m)(3)(ii), and (m)(3)(iii) of this AD was incorporated by reference in AD 2009-21-01. (i) Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 737-53-1168, dated March 16, 1995. (ii) Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 737-53-1168, Revision 1, dated August 17, 1995. (iii) Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 737-53-1168, Revision 2, dated November 27, 1996. (n) Alternative Methods of Compliance (AMOCs) (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 (o)(1) of this AD. Information may be emailed to: [email protected]. (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, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD. (4) AMOCs approved previously for repairs required by AD 2009- 21-01 are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (5) AMOCs approved previously for modifications done as optional terminating action for AD 2009-21-01 are approved as AMOCs for the skin panel replacement required by paragraph (l) of this AD. (o) Related Information (1) For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3) and (p)(4) of this AD. (p) Material Incorporated by Reference (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 Special Attention Service Bulletin 737-53-1168, Revision 4, dated June 3, 2015. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. (4) You may view this 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. (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. Issued in Renton, Washington, on May 2, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-10288 Filed 5-26-17; 8:45 am] BILLING CODE 4910-13-P
![24468 Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Rules and Regulations
(i) Related Information ACTION: Final rule. Engineer, Airframe Branch, ANM–120L,
Refer to MCAI European Aviation Safety FAA, Los Angeles Aircraft Certification
Agency (EASA) AD No.: 2016–0224, dated SUMMARY: We are superseding Office (ACO), 3960 Paramount
November 9, 2016, for related information. Airworthiness Directive (AD) 2009–21– Boulevard, Lakewood, CA 90712–4137;
The MCAI can be found in the AD docket on 01 for certain The Boeing Company phone: 562–627–5264; fax: 562–627–
the Internet at: https://www.regulations.gov/ Model 737–300 and 737–400 series 5210; email:
document?D=FAA-2017-0053-0002. airplanes. AD 2009–21–01 required jennifer.tsakoumakis@faa.gov.
(j) Material Incorporated by Reference repetitive inspections to detect cracking
of the aft fuselage skin, and related SUPPLEMENTARY INFORMATION:
(1) The Director of the Federal Register
approved the incorporation by reference investigative and corrective actions if Discussion
(IBR) of the service information listed in this necessary. This new AD adds certain
paragraph under 5 U.S.C. 552(a) and 1 CFR inspections, repairs, replacement, We issued a notice of proposed
part 51. related investigative and corrective rulemaking (NPRM) to amend 14 CFR
(2) You must use this service information actions if necessary; and removes part 39 to supersede AD 2009–21–01,
as applicable to do the actions required by certain airplanes from the applicability. Amendment 39–16038 (74 FR 52395,
this AD, unless the AD specifies otherwise. This AD was prompted by an evaluation October 13, 2009) (‘‘AD 2009–21–01’’).
(i) British Aerospace Jetstream Series 3100 AD 2009–21–01 applied to certain the
& 3200 Service Bulletin 32–A–JA851226, by the design approval holder (DAH)
indicating that the aft fuselage skin is Boeing Company Model 737–300 and
Revision 7, dated May 25, 2015. 737–400 series airplanes. The NPRM
(ii) Heroux Devtek Service Bulletin 32–19, subject to widespread fatigue damage
Revision 7, dated March 16, 2015. (WFD), and by reports of aft fuselage published in the Federal Register on
(3) For British Aerospace Regional Aircraft cracking. We are issuing this AD to May 13, 2016 (81 FR 29802). The NPRM
service information identified in this AD, address the unsafe condition on these was prompted by an evaluation by the
contact BAE Systems (Operations) Ltd, products. DAH indicating that the aft fuselage skin
Customer Information Department, Prestwick is subject to WFD, and by reports of aft
International Airport, Ayrshire, KA9 2RW, DATES: This AD is effective July 5, 2017. fuselage cracking. The NPRM proposed
Scotland, United Kingdom; phone: +44 1292 The Director of the Federal Register to continue to require repetitive
675207, fax: +44 1292 675704; email: approved the incorporation by reference inspections to detect cracking of the aft
RApublications@baesystems.com; Internet: of a certain publication listed in this AD
http://www.jetstreamcentral.com.
fuselage skin, and related investigative
as of July 5, 2017. and corrective actions if necessary. The
(4) You may review copies of the
referenced service information at the FAA, ADDRESSES: For service information NPRM also proposed to add new aft
Small Airplane Directorate, 901 Locust, identified in this final rule, contact fuselage skin inspections for cracking,
Kansas City, Missouri 64106. For information Boeing Commercial Airplanes, inspections to detect missing or loose
on the availability of this material at the Attention: Contractual & Data Services fasteners and any disbonding or
FAA, call (816) 329–4148. In addition, you (C&DS), 2600 Westminster Blvd., MC cracking of bonded doublers, permanent
can access this service information on the 110–SK57, Seal Beach, CA 90740–5600; repairs of time-limited repairs, related
Internet at http://www.regulations.gov by telephone 562–797–1717; Internet
searching for and locating Docket No. FAA–
investigative and corrective actions if
https://www.myboeingfleet.com. You necessary, and skin panel replacement.
2017–0053.
(5) You may view this service information may view this referenced service The NPRM also proposed to remove
that is incorporated by reference at the information at the FAA, Transport Model 737–400 series airplanes from the
National Archives and Records Airplane Directorate, 1601 Lind Avenue applicability. We are issuing this AD to
Administration (NARA). For information on SW., Renton, WA. For information on detect and correct cracking in the aft
the availability of this material at NARA, call the availability of this material at the fuselage skin along the longitudinal
202–741–6030, or go to: http:// FAA, call 425–227–1221. It is also edges of the chem-milled pockets in the
www.archives.gov/federal-register/cfr/ibr- available on the Internet at http://
locations.html.
bonded skin doubler, which could
www.regulations.gov by searching for result in possible rapid decompression
Issued in Kansas City, Missouri, on May and locating Docket No. FAA–2016– and reduced structural integrity of the
10, 2017. 6667. airplane.
Melvin Johnson, Examining the AD Docket Comments
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service. You may examine the AD docket on We gave the public the opportunity to
the Internet at http:// participate in developing this AD. The
[FR Doc. 2017–10408 Filed 5–26–17; 8:45 am]
www.regulations.gov by searching for following presents the comments
BILLING CODE 4910–13–P
and locating Docket No. FAA–2016– received on the NPRM and the FAA’s
6667; or in person at the Docket response to each comment.
DEPARTMENT OF TRANSPORTATION Management Facility between 9 a.m.
and 5 p.m., Monday through Friday, Request To Revise the Precipitating
except Federal holidays. The AD docket Event Statement
Federal Aviation Administration
contains this AD, the regulatory Boeing requested that we revise the
14 CFR Part 39 evaluation, any comments received, and precipitating event statement by
other information. The address for the including that there have been reports of
[Docket No. FAA–2016–6667; Directorate Docket Office (phone: 800–647–5527) is
Identifier 2015–NM–125–AD; Amendment aft fuselage cracking. Boeing stated that
39–18882; AD 2017–10–08]
Docket Management Facility, U.S. this revision would be consistent with
sradovich on DSK3GMQ082PROD with RULES
Department of Transportation, Docket wording of other related rulemaking.
RIN 2120–AA64 Operations, M–30, West Building We agree with Boeing’s request
Ground Floor, Room W12–140, 1200 because it provides additional clarity to
Airworthiness Directives; The Boeing New Jersey Avenue SE., Washington, the precipitating event statement. We
Company Airplanes DC 20590. have revised the SUMMARY and
AGENCY:Federal Aviation FOR FURTHER INFORMATION CONTACT: Discussion sections, and paragraph (e)
Administration (FAA), DOT. Jennifer Tsakoumakis, Aerospace of this AD accordingly.
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![Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Rules and Regulations 24471
the FAA amends 14 CFR part 39 as (g) Inspections, Related Investigative and (i) Do the applicable inspections to detect
follows: Corrective Actions missing or loose fasteners and any
At the applicable times specified in tables disbonding or cracking of bonded doublers,
PART 39—AIRWORTHINESS 1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of and do all applicable related investigative
SASB 737–53–1168, Revision 4, except as and corrective actions, in accordance with
DIRECTIVES
required by paragraphs (h)(1) and (h)(2) of the Accomplishment Instructions of SASB
this AD: Do the applicable inspections to 737–53–1168, Revision 4, except as required
■ 1. The authority citation for part 39 by paragraph (h)(3) of this AD. Do all
detect cracks in the aft fuselage skin panels,
continues to read as follows: and do all applicable related investigative applicable related investigative and
and corrective actions, in accordance with corrective actions before further flight.
Authority: 49 U.S.C. 106(g), 40113, 44701.
the Accomplishment Instructions of SASB Repeat the applicable inspections thereafter
§ 39.13 [Amended] 737–53–1168, Revision 4, except as required at the applicable intervals specified in SASB
by paragraphs (h)(3) and (h)(4) of this AD. Do 737–53–1168, Revision 4.
■ 2. The FAA amends § 39.13 by all applicable related investigative and (ii) Make the time-limited repair
removing Airworthiness Directive (AD) corrective actions before further flight. permanent, and do all applicable related
Repeat the applicable inspections thereafter investigative and corrective actions, in
2009–21–01, Amendment 39–16038 (74
at the applicable intervals specified in tables accordance with Part 6 of the
FR 52395, October 13, 2009), and Accomplishment Instructions of SASB 737–
adding the following new AD: 1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of
SASB 737–53–1168, Revision 4. 53–1168, Revision 4, except as required by
2017–10–08 The Boeing Company: Accomplishment of a repair in accordance paragraph (h)(3) of this AD. Do all applicable
Amendment 39–18882; Docket No. with ‘‘Part 4: Repair’’ of the Accomplishment related investigative and corrective actions
FAA–2016–6667; Directorate Identifier Instructions of SASB 737–53–1168, Revision before further flight. Accomplishing the
2015–NM–125–AD. 4, except as required by paragraph (h)(3) of permanent repair required by this paragraph
this AD, is terminating action for the terminates the inspections required by
(a) Effective Date repetitive inspections required by this paragraph (i)(1)(i) of this AD for the
This AD is effective July 5, 2017. paragraph at the repaired locations only. permanently repaired area only.
(2) For airplanes with a time-limited repair
(b) Affected ADs (h) Exceptions to SASB 737–53–1168, installed, as specified in SASB 737–53–1168,
Revision 4 Revision 4: At the applicable times specified
This AD replaces AD 2009–21–01,
Amendment 39–16038 (74 FR 52395, October (1) Where SASB 737–53–1168, Revision 4, in table 4 of paragraph 1.E., ‘‘Compliance,’’
specifies compliance times ‘‘after the of SASB 737–53–1168, Revision 4, do the
13, 2009) (‘‘AD 2009–21–01’’).
Revision 4 date of this service bulletin,’’ this actions specified in paragraphs (i)(2)(i) and
(c) Applicability AD requires compliance within the specified (i)(2)(ii) of this AD.
compliance times after the effective date of (i) Do the applicable inspections to detect
(1) This AD applies to The Boeing
this AD. missing or loose fasteners and any
Company Model 737–300 series airplanes,
(2) The Condition column of paragraph disbonding or cracking of bonded doublers,
certificated in any category, as identified in 1.E., ‘‘Compliance,’’ of SASB 737–53–1168, and do all applicable related investigative
Boeing Special Attention Service Bulletin Revision 4, refers to airplanes in certain and corrective actions, in accordance with
737–53–1168, Revision 4, dated June 3, 2015 configurations as of the ‘‘issue date of the Accomplishment Instructions of SASB
(‘‘SASB 737–53–1168, Revision 4’’). Revision 4 of this service bulletin.’’ However, 737–53–1168, Revision 4, except as required
(2) Installation of Supplemental Type this AD applies to airplanes in the specified by paragraph (h)(3) of this AD. Do all
Certificate (STC) ST01219SE (http:// configurations ‘‘as of the effective date of this applicable related investigative and
rgl.faa.gov/ AD.’’ corrective actions before further flight.
Regulatory_and_Guidance_Library/rgstc.nsf/ (3) Where SASB 737–53–1168, Revision 4, Repeat the applicable inspections thereafter
0/ebd1cec7b301293e86257cb30045557a/ specifies contacting Boeing for repair at the applicable intervals specified in table
$FILE/ST01219SE.pdf) does not affect the instructions or work instructions, before 4 of paragraph 1.E., ‘‘Compliance,’’ of SASB
ability to accomplish the actions required by further flight, repair or perform the work 737–53–1168, Revision 4.
this AD. Therefore, for airplanes on which instructions using a method approved in (ii) Make the time-limited repair
STC ST01219SE is installed, a ‘‘change in accordance with the procedures specified in permanent, and do all applicable related
product’’ alternative method of compliance paragraph (n) of this AD, except as required investigative and corrective actions, in
(AMOC) approval request is not necessary to by paragraph (h)(4) of this AD. accordance with Part 6 of the
comply with the requirements of 14 CFR (4) For airplanes on which an operator has Accomplishment Instructions of SASB 737–
39.17. a record that a skin panel was replaced with 53–1168, Revision 4, except as required by
a production skin panel before 53,000 total paragraph (h)(3) of this AD. Do all applicable
(d) Subject flight cycles: At the applicable time for the related investigative and corrective actions
Air Transport Association (ATA) of next inspection as specified in tables 1 and before further flight. Accomplishing the
America Code 53, Fuselage. 2 of paragraph 1.E., ‘‘Compliance,’’ of SASB permanent repair required by this paragraph
737–53–1168, Revision 4, except as provided terminates the inspections required by
(e) Unsafe Condition by paragraph (h)(1) and (h)(2) of this AD, paragraph (i)(2)(i) of this AD for the
This AD was prompted by an evaluation by perform inspections and applicable permanently repaired area only.
the design approval holder (DAH) indicating corrective actions using a method approved
(j) Modification of Certain Permanent
in accordance with the procedures specified
that the aft fuselage skin is subject to Repairs
in paragraph (n) of this AD.
widespread fatigue damage (WFD), and For airplanes with an existing time-limited
reports of aft fuselage cracking. We are (i) Actions for Airplanes With a Time- repair that was made permanent, as specified
issuing this AD to detect and correct cracking Limited Repair Installed in Boeing Service Bulletin 737–53–1168,
in the aft fuselage skin along the longitudinal (1) For airplanes with a time-limited repair Revision 3, dated November 28, 2006: At the
edges of the chem-milled pockets in the installed, as specified in Boeing Service applicable times specified in table 5 of
sradovich on DSK3GMQ082PROD with RULES
bonded skin doubler, which could result in Bulletin 737–53–1168, Revision 3, dated paragraph 1.E., ‘‘Compliance,’’ of SASB 737–
possible rapid decompression and reduced November 28, 2006: At the applicable times 53–1168, Revision 4, except as provided by
structural integrity of the airplane. specified in table 3 of paragraph 1.E., paragraphs (h)(1) of this AD, modify the
‘‘Compliance,’’ of SASB 737–53–1168, existing permanent repair, and do all
(f) Compliance
Revision 4, except as provided by paragraphs applicable related investigative and
Comply with this AD within the (h)(1) and (h)(2) of this AD, do the actions corrective actions, in accordance with Part 6
compliance times specified, unless already specified in paragraphs (i)(1)(i) and (i)(1)(ii) of the Accomplishment Instructions of SASB
done. of this AD. 737–53–1168, Revision 4, except as required
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![24472 Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Rules and Regulations
by paragraph (h)(3) of this AD. Do all AD. The service information specified in (2) You must use this service information
applicable related investigative and paragraphs (m)(3)(i), (m)(3)(ii), and (m)(3)(iii) as applicable to do the actions required by
corrective actions before further flight. of this AD was incorporated by reference in this AD, unless the AD specifies otherwise.
AD 2009–21–01. (i) Boeing Special Attention Service
(k) Post-Repair Inspections
(i) Part 3 of the Accomplishment Bulletin 737–53–1168, Revision 4, dated June
Table 6 of paragraph 1.E., ‘‘Compliance,’’ Instructions of Boeing Service Bulletin 737– 3, 2015.
of SASB 737–53–1168, Revision 4, specifies 53–1168, dated March 16, 1995. (ii) Reserved.
post-repair airworthiness limitation (ii) Part 3 of the Accomplishment (3) For Boeing service information
inspections in compliance with 14 CFR Instructions of Boeing Service Bulletin 737– identified in this AD, contact Boeing
25.571(a)(3) at the repaired locations, which 53–1168, Revision 1, dated August 17, 1995. Commercial Airplanes, Attention:
support compliance with 14 CFR (iii) Part 3 of the Accomplishment Contractual & Data Services (C&DS), 2600
121.1109(c)(2) or 129.109(b)(2). As Instructions of Boeing Service Bulletin 737– Westminster Blvd., MC 110–SK57, Seal
airworthiness limitations, these inspections 53–1168, Revision 2, dated November 27, Beach, CA 90740–5600; telephone 562–797–
are required by maintenance and operational 1996. 1717; Internet https://
rules. It is therefore unnecessary to mandate www.myboeingfleet.com.
them in this AD. Deviations from these (n) Alternative Methods of Compliance (4) You may view this service information
inspections require FAA approval, but do not (AMOCs) at the FAA, Transport Airplane Directorate,
require an AMOC. (1) The Manager, Los Angeles Aircraft 1601 Lind Avenue SW., Renton, WA. For
(l) Skin Panel Replacement Certification Office (ACO), FAA, has the information on the availability of this
authority to approve AMOCs for this AD, if material at the FAA, call 425–227–1221.
At the later of the times specified in
requested using the procedures found in 14 (5) You may view this service information
paragraphs (l)(1), (1)(2), and (l)(3) of this AD:
CFR 39.19. In accordance with 14 CFR 39.19, that is incorporated by reference at the
Replace the applicable skin panels, and do
send your request to your principal inspector National Archives and Records
all applicable related investigative and
or local Flight Standards District Office, as Administration (NARA). For information on
corrective actions, in accordance with the
appropriate. If sending information directly the availability of this material at NARA, call
Accomplishment Instructions of SASB 737–
to the manager of the ACO, send it to the 202–741–6030, or go to: http://
53–1168, Revision 4. Do all applicable
attention of the person identified in www.archives.gov/federal-register/cfr/ibr-
related investigative and corrective actions
before further flight. Doing the skin panel paragraph (o)(1) of this AD. Information may locations.html.
replacement required by this paragraph be emailed to: 9-ANM-LAACO-AMOC-
Issued in Renton, Washington, on May 2,
terminates the inspection requirements of Requests@faa.gov.
2017.
paragraphs (g), (i), and (j) of this AD for that (2) Before using any approved AMOC,
notify your appropriate principal inspector, Michael Kaszycki,
skin panel only, provided the skin panel
or lacking a principal inspector, the manager Acting Manager, Transport Airplane
replacement was done with a production
of the local flight standards district office/ Directorate, Aircraft Certification Service.
skin panel after 53,000 total flight cycles.
(1) Before 60,000 total flight cycles, but not certificate holding district office. [FR Doc. 2017–10288 Filed 5–26–17; 8:45 am]
before 53,000 total flight cycles. (3) An AMOC that provides an acceptable BILLING CODE 4910–13–P
(2) Within 6,000 flight cycles after the level of safety may be used for any repair,
effective date of this AD, but not before modification, or alteration required by this
53,000 total flight cycles. AD if it is approved by the Boeing
Commercial Airplanes Organization
DEPARTMENT OF TRANSPORTATION
(3) If the skin panel is replaced with a
production skin panel, not before 53,000 total Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
Federal Aviation Administration
flight cycles. If the skin panel is replaced
with a kit skin panel as specified in SASB ACO, to make those findings. To be
approved, the repair method, modification 14 CFR Part 39
737–53–1168, Revision 4, the 53,000 total
flight cycle limit does not apply. deviation, or alteration deviation must meet [Docket No. FAA–2017–0156; Directorate
the certification basis of the airplane and the Identifier 2017–CE–003–AD; Amendment
(m) Credit for Previous Actions approval must specifically refer to this AD. 39–18877; AD 2017–10–03]
(1) This paragraph provides credit for the (4) AMOCs approved previously for repairs
actions required by paragraph (g) of this AD, required by AD 2009–21–01 are approved as RIN 2120–AA64
if those actions were performed before the AMOCs for the corresponding provisions of
effective date of this AD using Boeing Service paragraph (g) of this AD. Airworthiness Directives; ZLIN
Bulletin 737–53–1168, Revision 3, dated (5) AMOCs approved previously for AIRCRAFT a.s. Airplanes
November 28, 2006, except as required by modifications done as optional terminating
paragraph (h)(4) of this AD. Boeing Service action for AD 2009–21–01 are approved as AGENCY: Federal Aviation
Bulletin 737–53–1168, Revision 3, dated AMOCs for the skin panel replacement Administration (FAA), Department of
November 28, 2006, was incorporated by required by paragraph (l) of this AD. Transportation (DOT).
reference in AD 2009–21–01. ACTION: Final rule.
(2) This paragraph provides credit for the (o) Related Information
actions required by paragraph (l) of this AD, (1) For more information about this AD, SUMMARY: We are superseding
if those actions were performed before the contact Jennifer Tsakoumakis, Aerospace Airworthiness Directive (AD) 2003–11–
effective date of this AD using Boeing Service Engineer, Airframe Branch, ANM–120L,
12 for ZLIN AIRCRAFT a.s. Model Z–
Bulletin 737–53–1168, Revision 3, dated FAA, Los Angeles ACO, 3960 Paramount
November 28, 2006, except as required by Boulevard, Lakewood, CA 90712–4137; 242L airplanes (type certificate
paragraph (h)(4) of this AD. Boeing Service phone: 562–627–5264; fax: 562–627–5210; previously held by MORAVAN a.s.).
Bulletin 737–53–1168, Revision 3, dated email: jennifer.tsakoumakis@faa.gov. This AD results from mandatory
November 28, 2006, was incorporated by (2) Service information identified in this continuing airworthiness information
reference in AD 2009–21–01. AD that is not incorporated by reference is (MCAI) issued by an aviation authority
(3) This paragraph provides credit for the available at the addresses specified in of another country to identify and
sradovich on DSK3GMQ082PROD with RULES
actions required by paragraph (l) of this AD, paragraphs (p)(3) and (p)(4) of this AD. correct an unsafe condition on an
if those actions were performed before aviation product. The MCAI describes
November 17, 2009 (the effective date of AD (p) Material Incorporated by Reference
2009–21–01), using any service information (1) The Director of the Federal Register the unsafe condition as a need to
specified in paragraphs (m)(3)(i), (m)(3)(ii), approved the incorporation by reference incorporate new revisions into the
and (m)(3)(iii) of this AD, provided the (IBR) of the service information listed in this Limitations section, Chapter 9, of the
replacement is made with a kit skin panel, paragraph under 5 U.S.C. 552(a) and 1 CFR FAA-approved maintenance program
except as required by paragraph (h)(4) of this part 51. (e.g., maintenance manual) to impose
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Document Created: 2018-11-08 08:55:44
Document Modified: 2018-11-08 08:55:44
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective July 5, 2017. | |
| Contact | Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 82 FR 24468 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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