81 FR 1577 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 8 (January 13, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 8 (January 13, 2016)
| Page Range | 1577-1579 | |
| FR Document | 2015-33172 |
[Federal Register Volume 81, Number 8 (Wednesday, January 13, 2016)] [Proposed Rules] [Pages 1577-1579] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-33172] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-8429; Directorate Identifier 2015-NM-122-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747- 200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This proposed AD was prompted by reports of fatigue cracks in the station 320 crown frame and in window post number 3. This proposed AD would require repetitive inspections for cracks and missing fasteners of the station 320 crown frame, cracks in the web and flange surfaces of the forward segment of window post number 3, and missing fasteners and cracks of the window upper sill; post- modification inspections for cracks of the window upper sill; one-time fastener rework; and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct fatigue cracking and missing fasteners of the station 320 crown frame, cracking of the window post number 3, and cracking of the window upper sill, which could result in an in-flight decompression and a loss of structural integrity of the fuselage. DATES: We must receive comments on this proposed AD by February 29, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 8429. 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-2015- 8429; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-8429; Directorate Identifier 2015-NM-122-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of fatigue cracks in the station 320 crown frame on Model 747-400 series airplanes. Other Model 747 airplanes, except Model 747-8F and 747-8 airplanes, are of a similar station 320 crown frame configuration. Inner chord cracks of 0.03- to 0.22-inch in length have been found on 15 airplanes with total flight cycles ranging from 11,498 to 31,315. Also, a 1.8-inch crack was found in the outboard web of the frame on one airplane with 14,749 total flight cycles. Cracks have also been found in window post number 3, which connects to the lower end of the inner chord of the station 320 crown frame. Cracks of 0.03- to 0.11-inch in length have been found in window post number 3 on five airplanes with total flight cycles ranging from 12,329 to 15,772. Additionally, fatigue cracks that had extended to fully sever the inner chord and outboard web of the frame were found on the Model 747- 400 fatigue test airplane at 38,333 total pressure cycles, and significant cracks were found in both the frame inner chord and outboard web at 30,500 total pressure cycles on the Model 747-100SR fatigue test airplane. Fatigue cracking and missing fasteners of the station 320 crown frame, cracking of the window post number 3, and cracking of the window upper sill could result in in-flight decompression and a loss of structural integrity of the fuselage. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015. The service information describes procedures for inspections and corrective actions for cracks and missing fasteners in the inner chord and outboard webs of the station 320 crown frame, in the left and right side window post number 3, and in the upper sill structure. 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 of this NPRM. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or [[Page 1578]] develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions identified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-8429. The phrase ``related investigative actions'' is used in this proposed AD. ``Related investigative actions'' are follow-on actions that (1) are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. ``Corrective actions'' are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Explanation of ``RC'' Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service information is expected to improve an owner's/operator's understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The steps identified as Required for Compliance (RC) in any service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. For service information that contains steps that are labeled as RC, the following provisions apply: (1) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD, and an alternative method of compliance (AMOC) is required for any deviations to RC steps, including substeps and identified figures; and (2) steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. Costs of Compliance We estimate that this proposed AD affects 165 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections.............. Up to 193 work-hours x $0 Up to $16,405 per Up to $2,706,825 $85 per hour = $16,405 inspection cycle. per inspection per inspection cycle. cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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 determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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. [[Page 1579]] Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA-2015-8429; Directorate Identifier 2015-NM-122-AD. (a) Comments Due Date We must receive comments by February 29, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747- 400D, 747-400F, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747- 53A2862, Revision 1, dated July 24, 2015. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of fatigue cracks in the station 320 crown frame in window post number 3. We are issuing this AD to detect and correct fatigue cracking and missing fasteners of the station 320 crown frame, cracking of the window post number 3, and cracking of the window upper sill, which could result in an in- flight decompression and a loss of structural integrity of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Initial Inspections, Related Investigative Actions, and Corrective Actions At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015, except as provided by paragraphs (j)(1) and (j)(2) of this AD: Do the actions specified in paragraphs (g)(1) through (g)(5) of this AD; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2862, Revision 1, dated July 24, 2015, except as required by paragraph (j)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. (1) Do a detailed inspection for cracks and missing fasteners of the station 320 crown frame. (2) Do a surface high frequency eddy current (HFEC) inspection for cracks of the station 320 crown frame. (3) Do a surface HFEC inspection for cracks in the web and flange surfaces of the forward segment of window post number 3. (4) Do a detailed inspection for missing fasteners of the window upper sill. (5) Do a surface HFEC inspection for cracks of the window upper sill. (h) Repetitive Inspections and Post-Repair Inspections, Related Investigative Actions, and Corrective Actions Do applicable repetitive post-repair inspections and repeat the inspections specified in paragraphs (g)(1) through (g)(5) of this AD for cracking in the window upper sill thereafter at the applicable compliance time and intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2862, Revision 1, dated July 24, 2015, except as required by paragraph (j)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. (i) Fastener Rework, Related Investigative Actions, and Corrective Actions At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015: Do the applicable actions (including fastener rework and a detailed inspection of the condition of the fastener hole) specified in Part 11 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2862, Revision 1, dated July 24, 2015; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2862, Revision 1, dated July 24, 2015. Do all applicable related investigative and corrective actions before further flight. (j) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015, specifies a compliance time ``after the original date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015, specifies a compliance time ``after the Revision 1 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (3) Where Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015, specifies to contact Boeing for repairs: Before further flight, repair, using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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 (l)(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 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) Except as required by paragraphs (g), (h), and (j)(3) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6432; fax: 425-917-6590; email: [email protected]. (2) 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. Issued in Renton, Washington, on December 23, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-33172 Filed 1-12-16; 8:45 am] BILLING CODE 4910-13-P
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Issued in Renton, Washington, on Room W12–140, 1200 New Jersey www.regulations.gov, including any
December 23, 2015. Avenue SE., Washington, DC 20590. personal information you provide. We
John P. Piccola, Jr., • Hand Delivery: Deliver to Mail will also post a report summarizing each
Acting Manager, Transport Airplane address above between 9 a.m. and 5 substantive verbal contact we receive
Directorate, Aircraft Certification Service. p.m., Monday through Friday, except about this proposed AD.
[FR Doc. 2015–33175 Filed 1–12–16; 8:45 am] Federal holidays.
For service information identified in Discussion
BILLING CODE 4910–13–P
this proposed AD, contact Boeing We have received reports of fatigue
Commercial Airplanes, Attention: Data cracks in the station 320 crown frame on
DEPARTMENT OF TRANSPORTATION & Services Management, P.O. Box 3707, Model 747–400 series airplanes. Other
MC 2H–65, Seattle, WA 98124–2207; Model 747 airplanes, except Model 747–
Federal Aviation Administration telephone 206–544–5000, extension 1; 8F and 747–8 airplanes, are of a similar
fax 206–766–5680; Internet https:// station 320 crown frame configuration.
14 CFR Part 39 www.myboeingfleet.com. You may view Inner chord cracks of 0.03- to 0.22-inch
this referenced service information at in length have been found on 15
[Docket No. FAA–2015–8429; Directorate
Identifier 2015–NM–122–AD] the FAA, Transport Airplane airplanes with total flight cycles ranging
Directorate, 1601 Lind Avenue SW., from 11,498 to 31,315. Also, a 1.8-inch
RIN 2120–AA64 Renton, WA. For information on the crack was found in the outboard web of
availability of this material at the FAA, the frame on one airplane with 14,749
Airworthiness Directives; The Boeing call 425–227–1221. It is also available total flight cycles.
Company Airplanes on the Internet at http:// Cracks have also been found in
AGENCY: Federal Aviation www.regulations.gov by searching for window post number 3, which connects
Administration (FAA), DOT. and locating Docket No. FAA–2015– to the lower end of the inner chord of
8429. the station 320 crown frame. Cracks of
ACTION: Notice of proposed rulemaking
(NPRM). Examining the AD Docket 0.03- to 0.11-inch in length have been
found in window post number 3 on five
SUMMARY: We propose to adopt a new You may examine the AD docket on airplanes with total flight cycles ranging
airworthiness directive (AD) for certain the Internet at http:// from 12,329 to 15,772.
The Boeing Company Model 747–100, www.regulations.gov by searching for Additionally, fatigue cracks that had
747–100B, 747–100B SUD, 747–200B, and locating Docket No. FAA–2015– extended to fully sever the inner chord
747–200C, 747–200F, 747–300, 747– 8429; or in person at the Docket and outboard web of the frame were
400, 747–400D, 747–400F, 747SR, and Management Facility between 9 a.m. found on the Model 747–400 fatigue test
747SP series airplanes. This proposed and 5 p.m., Monday through Friday, airplane at 38,333 total pressure cycles,
except Federal holidays. The AD docket and significant cracks were found in
AD was prompted by reports of fatigue
contains this proposed AD, the both the frame inner chord and
cracks in the station 320 crown frame
regulatory evaluation, any comments outboard web at 30,500 total pressure
and in window post number 3. This
received, and other information. The cycles on the Model 747–100SR fatigue
proposed AD would require repetitive
street address for the Docket Office test airplane.
inspections for cracks and missing
(phone: 800–647–5527) is in the Fatigue cracking and missing
fasteners of the station 320 crown frame,
ADDRESSES section. Comments will be fasteners of the station 320 crown frame,
cracks in the web and flange surfaces of
available in the AD docket shortly after cracking of the window post number 3,
the forward segment of window post
receipt. and cracking of the window upper sill
number 3, and missing fasteners and
FOR FURTHER INFORMATION CONTACT: Bill could result in in-flight decompression
cracks of the window upper sill; post-
modification inspections for cracks of Ashforth, Aerospace Engineer, Airframe and a loss of structural integrity of the
the window upper sill; one-time Branch, ANM–120S, FAA, Seattle fuselage.
fastener rework; and related Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057– Related Service Information Under
investigative and corrective actions if 1 CFR Part 51
necessary. We are proposing this AD to 3356; phone: 425–917–6432; fax: 425–
detect and correct fatigue cracking and 917–6590; email: Bill.Ashforth@faa.gov. We reviewed Boeing Alert Service
missing fasteners of the station 320 SUPPLEMENTARY INFORMATION: Bulletin 747–53A2862, Revision 1,
crown frame, cracking of the window dated July 24, 2015. The service
Comments Invited information describes procedures for
post number 3, and cracking of the
We invite you to send any written inspections and corrective actions for
window upper sill, which could result
relevant data, views, or arguments about cracks and missing fasteners in the
in an in-flight decompression and a loss
this proposal. Send your comments to inner chord and outboard webs of the
of structural integrity of the fuselage.
an address listed under the ADDRESSES station 320 crown frame, in the left and
DATES: We must receive comments on section. Include ‘‘Docket No. FAA– right side window post number 3, and
this proposed AD by February 29, 2016. 2015–8429; Directorate Identifier 2015– in the upper sill structure. This service
ADDRESSES: You may send comments, NM–122–AD’’ at the beginning of your information is reasonably available
using the procedures found in 14 CFR comments. We specifically invite because the interested parties have
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
11.43 and 11.45, by any of the following comments on the overall regulatory, access to it through their normal course
methods: economic, environmental, and energy of business or by the means identified
• Federal eRulemaking Portal: Go to aspects of this proposed AD. We will in the ADDRESSES section of this NPRM.
http://www.regulations.gov. Follow the consider all comments received by the
instructions for submitting comments. closing date and may amend this FAA’s Determination
• Fax: 202–493–2251. proposed AD because of those We are proposing this AD because we
• Mail: U.S. Department of comments. evaluated all the relevant information
Transportation, Docket Operations, We will post all comments we and determined the unsafe condition
M–30, West Building Ground Floor, receive, without change, to http:// described previously is likely to exist or
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§ 39.13 [Amended] (h) Repetitive Inspections and Post-Repair be emailed to: 9-ANM-Seattle-ACO-AMOC-
■ 2. The FAA amends § 39.13 by adding Inspections, Related Investigative Actions, Requests@faa.gov.
the following new airworthiness and Corrective Actions (2) Before using any approved AMOC,
directive (AD): Do applicable repetitive post-repair notify your appropriate principal inspector,
inspections and repeat the inspections or lacking a principal inspector, the manager
The Boeing Company: Docket No. FAA– specified in paragraphs (g)(1) through (g)(5) of the local flight standards district office/
2015–8429; Directorate Identifier 2015– of this AD for cracking in the window upper
NM–122–AD. certificate holding district office.
sill thereafter at the applicable compliance (3) An AMOC that provides an acceptable
(a) Comments Due Date time and intervals specified in paragraph level of safety may be used for any repair,
1.E., ‘‘Compliance,’’ of Boeing Alert Service
We must receive comments by February modification, or alteration required by this
Bulletin 747–53A2862, Revision 1, dated July
29, 2016. AD if it is approved the Boeing Commercial
24, 2015; and do all applicable related
(b) Affected ADs investigative and corrective actions; in Airplanes Organization Designation
accordance with the Accomplishment Authorization (ODA) that has been
None.
Instructions of Boeing Alert Service Bulletin authorized by the Manager, Seattle ACO, to
(c) Applicability 747–53A2862, Revision 1, dated July 24, make those findings. To be approved, the
This AD applies to The Boeing Company 2015, except as required by paragraph (j)(3) repair method, modification deviation, or
Model 747–100, 747–100B, 747–100B SUD, of this AD. Do all applicable related alteration deviation must meet the
747–200B, 747–200C, 747–200F, 747–300, investigative and corrective actions before certification basis of the airplane, and the
747–400, 747–400D, 747–400F, 747SR, and further flight.
approval must specifically refer to this AD.
747SP series airplanes, certificated in any (i) Fastener Rework, Related Investigative (4) Except as required by paragraphs (g),
category, as identified in Boeing Alert Actions, and Corrective Actions (h), and (j)(3) of this AD: For service
Service Bulletin 747–53A2862, Revision 1,
At the applicable time specified in information that contains steps that are
dated July 24, 2015.
paragraph 1.E., ‘‘Compliance,’’ of Boeing labeled as Required for Compliance (RC), the
(d) Subject Alert Service Bulletin 747–53A2862, provisions of paragraphs (k)(4)(i) and
Air Transport Association (ATA) of Revision 1, dated July 24, 2015: Do the (k)(4)(ii) apply.
America Code 53, Fuselage. applicable actions (including fastener rework (i) The steps labeled as RC, including
and a detailed inspection of the condition of substeps under an RC step and any figures
(e) Unsafe Condition the fastener hole) specified in Part 11 of the identified in an RC step, must be done to
This AD was prompted by reports of Accomplishment Instructions of Boeing Alert
comply with the AD. An AMOC is required
fatigue cracks in the station 320 crown frame Service Bulletin 747–53A2862, Revision 1,
dated July 24, 2015; and do all applicable for any deviations to RC steps, including
in window post number 3. We are issuing
this AD to detect and correct fatigue cracking related investigative and corrective actions; substeps and identified figures.
and missing fasteners of the station 320 in accordance with the Accomplishment (ii) Steps not labeled as RC may be
crown frame, cracking of the window post Instructions of Boeing Alert Service Bulletin deviated from using accepted methods in
number 3, and cracking of the window upper 747–53A2862, Revision 1, dated July 24, accordance with the operator’s maintenance
sill, which could result in an in-flight 2015. Do all applicable related investigative or inspection program without obtaining
decompression and a loss of structural and corrective actions before further flight. approval of an AMOC, provided the RC steps,
integrity of the fuselage. including substeps and identified figures, can
(j) Exceptions to Service Information
(f) Compliance Specifications still be done as specified, and the airplane
can be put back in an airworthy condition.
Comply with this AD within the (1) Where Boeing Alert Service Bulletin
compliance times specified, unless already 747–53A2862, Revision 1, dated July 24, (l) Related Information
done. 2015, specifies a compliance time ‘‘after the
original date of this service bulletin,’’ this AD (1) For more information about this AD,
(g) Initial Inspections, Related Investigative requires compliance within the specified contact Bill Ashforth, Aerospace Engineer,
Actions, and Corrective Actions compliance time after the effective date of Airframe Branch, ANM–120S, FAA, Seattle
At the applicable time specified in this AD. Aircraft Certification Office (ACO), 1601 Lind
paragraph 1.E., ‘‘Compliance,’’ of Boeing (2) Where Boeing Alert Service Bulletin Avenue SW., Renton, WA 98057–3356;
Alert Service Bulletin 747–53A2862, 747–53A2862, Revision 1, dated July 24, phone: 425–917–6432; fax: 425–917–6590;
Revision 1, dated July 24, 2015, except as 2015, specifies a compliance time ‘‘after the email: Bill.Ashforth@faa.gov.
provided by paragraphs (j)(1) and (j)(2) of this Revision 1 date of this service bulletin,’’ this (2) For service information identified in
AD: Do the actions specified in paragraphs AD requires compliance within the specified this AD, contact Boeing Commercial
(g)(1) through (g)(5) of this AD; and do all compliance time after the effective date of Airplanes, Attention: Data & Services
applicable related investigative and this AD.
Management, P.O. Box 3707, MC 2H–65,
corrective actions; in accordance with the (3) Where Boeing Alert Service Bulletin
Accomplishment Instructions of Boeing Alert Seattle, WA 98124–2207; telephone 206–
747–53A2862, Revision 1, dated July 24,
Service Bulletin 747–53A2862, Revision 1, 2015, specifies to contact Boeing for repairs: 544–5000, extension 1; fax 206–766–5680;
dated July 24, 2015, except as required by Before further flight, repair, using a method Internet https://www.myboeingfleet.com. You
paragraph (j)(3) of this AD. Do all applicable approved in accordance with the procedures may view this referenced service information
related investigative and corrective actions specified in paragraph (k) of this AD. at the FAA, Transport Airplane Directorate,
before further flight. 1601 Lind Avenue SW., Renton, WA. For
(1) Do a detailed inspection for cracks and (k) Alternative Methods of Compliance
information on the availability of this
missing fasteners of the station 320 crown (AMOCs)
material at the FAA, call 425–227–1221.
frame. (1) The Manager, Seattle Aircraft
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(2) Do a surface high frequency eddy Certification Office (ACO), FAA, has the Issued in Renton, Washington, on
current (HFEC) inspection for cracks of the authority to approve AMOCs for this AD, if December 23, 2015.
station 320 crown frame. requested using the procedures found in 14 John P. Piccola, Jr.,
(3) Do a surface HFEC inspection for cracks CFR 39.19. In accordance with 14 CFR 39.19,
Acting Manager, Transport Airplane
in the web and flange surfaces of the forward send your request to your principal inspector
or local Flight Standards District Office, as Directorate, Aircraft Certification Service.
segment of window post number 3.
(4) Do a detailed inspection for missing appropriate. If sending information directly [FR Doc. 2015–33172 Filed 1–12–16; 8:45 am]
fasteners of the window upper sill. to the manager of the ACO, send it to the BILLING CODE 4910–13–P
(5) Do a surface HFEC inspection for cracks attention of the person identified in
of the window upper sill. paragraph (l)(1) of this AD. Information may
VerDate Sep<11>2014 16:20 Jan 12, 2016 Jkt 238001 PO 00000 Frm 00017 Fmt 4702 Sfmt 9990 E:\FR\FM\13JAP1.SGM 13JAP1](https://thefederalregister.org/doc/81_FR_1585/page/3.svg)
Document Created: 2016-01-13 01:01:08
Document Modified: 2016-01-13 01:01:08
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by February 29, 2016. | |
| Contact | Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 1577 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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