81 FR 59532 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 168 (August 30, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 168 (August 30, 2016)
| Page Range | 59532-59535 | |
| FR Document | 2016-20683 |
[Federal Register Volume 81, Number 168 (Tuesday, August 30, 2016)] [Proposed Rules] [Pages 59532-59535] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-20683] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9050; Directorate Identifier 2016-NM-086-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. [[Page 59533]] ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, -400D, and -400F series airplanes. This proposed AD was prompted by widespread corrosion damage that was found on the skin inner surface along the upper bulkhead at certain stations between certain stringers. This proposed AD would require repetitive inspections of the fuselage crown skin inner surface, and related investigative and corrective actions if necessary. This AD would also allow for terminating actions for some of the repetitive inspections. We are proposing this AD to detect and correct cracks and corrosion on the crown skin inner surface. If the cracks or corrosion are not repaired, the cracks can rapidly join together and can cause a sudden decompression and loss of structural integrity of the airplane. DATES: We must receive comments on this proposed AD by October 14, 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 NPRM, 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-2016-9050. 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- 9050; 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: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6428; 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-2016-9050; Directorate Identifier 2016-NM-086-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 received a report indicating that operators have experienced widespread corrosion damage that was found on the skin inner surface along the upper bulkhead at station (STA) 1480 between stringers S-15L and S-16R, on the fuselage skin inner surface aft of the STA 1350 frame between stringers S-15 and S-16R and between stringers S-17 and S-18R, and on the skin inner surface aft of the STA 1283 frame between stringers S-5L and S-8L. This condition, if not corrected, could result in cracks that could rapidly join together and can cause a sudden decompression and loss of structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016. The service information describes procedures for inspecting the fuselage crown skin inner surface body at affected stations, and related investigative and corrective actions if necessary. 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. 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 develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between the 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-2016-9050. 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 action, 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 correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between the Proposed AD and the Service Information Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016, specifies to contact the manufacturer for certain instructions, but this proposed AD would require accomplishment of repair methods, modification deviations, and alteration deviations 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. [[Page 59534]] Costs of Compliance We estimate that this proposed AD affects 53 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Cost per product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- Inspections and access............... Up to 815 Up to $69,275.......... Up to $3,671,575. work[dash]hours x $85 per hour = $69,275. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these repairs and on-condition inspections: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Repairs and on[dash]condition Up to 1,820 N/A.................... Up to $154,700. inspections. work[dash]hours x $85 per hour = $154,700. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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. 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-2016-9050; Directorate Identifier 2016-NM-086-AD. (a) Comments Due Date We must receive comments by October 14, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747-400, -400D, and -400F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by widespread corrosion damage that was found on the skin inner surface along the upper bulkhead at certain stations between certain stringers. We are issuing this AD to detect and correct cracks and corrosion on the crown skin inner surface. If the cracks or corrosion are not repaired, the cracks can rapidly join together and can cause a sudden decompression and loss of structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of the Skin Inner Surface At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016, except as required by paragraph (k)(1) of this AD: Do a detailed inspection of the skin inner surface for any missing or degraded finish, sign of corrosion, or crack, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2878, dated May 19, 2016. Repeat the inspection thereafter at intervals not to exceed the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016, until the actions specified in paragraph (i) of this AD have been done. [[Page 59535]] (h) Repair of the Skin Inner Surface If any damage is found during any inspection required by paragraph (g) of this AD, before further flight, do all applicable related investigative and correction actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2878, dated May 19, 2016, except as required by paragraph (k)(2) of this AD. (i) Terminating Action Modification or repair of the inner skin surfaces in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2878, May 19, 2016, terminates the repetitive inspections required by paragraph (g) of this AD. (j) Post Repair Inspection and Repairs For airplanes on which a repair or modification has been done in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016: Except as required by paragraph (k)(1) of this AD, at the applicable time specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016, do detailed inspections to detect damage of the repaired or modified areas, and do all applicable corrective actions, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2878, May 19, 2016, except as required by paragraph (k)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspections thereafter at intervals not to exceed the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016. (k) Exceptions (1) Where Boeing Alert Service Bulletin 747-53A2878, May 19, 2016, specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any cracking or corrosion is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747-53A2878, May 19, 2016, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking or corrosion using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (l) 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 (m)(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) Except as required by paragraph (k)(1) and (k)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (l)(4)(i) and (l)(4)(ii) of this AD 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. (m) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 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 August 18, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-20683 Filed 8-29-16; 8:45 am] BILLING CODE 4910-13-P
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Part A, Subpart III, Section 44701: (b) Affected ADs standards district office/certificate holding
General requirements.’’ Under that None. district office. The AMOC approval letter
section, Congress charges the FAA with must specifically reference this AD.
(c) Applicability (2) Contacting the Manufacturer: For any
promoting safe flight of civil aircraft in requirement in this AD to obtain corrective
air commerce by prescribing regulations This AD applies to all Airbus Model A300
B4–603, B4–620, and B4–622 airplanes; actions from a manufacturer, the action must
for practices, methods, and procedures Model A300 B4–605R and A300 B4–622R be accomplished using a method approved
the Administrator finds necessary for airplanes; and Model A300 C4–605R Variant by the Manager, International Branch, ANM–
safety in air commerce. This regulation F airplanes, certificated in any category. 116, Transport Airplane Directorate, FAA; or
is within the scope of that authority the EASA; or Airbus’s EASA Design
(d) Subject Organization Approval (DOA). If approved by
because it addresses an unsafe condition
Air Transport Association (ATA) of the DOA, the approval must include the
that is likely to exist or develop on DOA-authorized signature.
products identified in this rulemaking America Code 53, Fuselage.
(3) Required for Compliance (RC): Except
action. (e) Reason as required by paragraph (h) of this AD: If
This AD was prompted by an in-service any service information contains procedures
Regulatory Findings
detection of cracks in the fuselage skin lap or tests that are identified as RC, those
We determined that this proposed AD joints. We are issuing this AD to detect and procedures and tests must be done to comply
would not have federalism implications correct cracks in the skin lap joint below with this AD; any procedures or tests that are
stringer 28 at frame (FR) 72 to FR 76. Such not identified as RC are recommended. Those
under Executive Order 13132. This
cracking could result in reduced structural procedures and tests that are not identified
proposed AD would not have a as RC may be deviated from using accepted
integrity of the airplane.
substantial direct effect on the States, on methods in accordance with the operator’s
the relationship between the national (f) Compliance maintenance or inspection program without
Government and the States, or on the Comply with this AD within the obtaining approval of an AMOC, provided
distribution of power and compliance times specified, unless already the procedures and tests identified as RC can
responsibilities among the various done. be done and the airplane can be put back in
levels of government. an airworthy condition. Any substitutions or
(g) Repetitive Inspections changes to procedures or tests identified as
For the reasons discussed above, I Before 29,500 flight cycles since the first RC require approval of an AMOC.
certify this proposed regulation: flight of the airplane or within 2,000 flight
1. Is not a ‘‘significant regulatory (j) Related Information
cycles after the effective date of this AD,
action’’ under Executive Order 12866; whichever occurs later, do an ultrasonic (1) Refer to Mandatory Continuing
inspection for cracks of the skin lap joint Airworthiness Information (MCAI) EASA AD
2. Is not a ‘‘significant rule’’ under the
below stringer 28 at FR 72 to FR 76 and do 2016–0557, dated March 18, 2016, for related
DOT Regulatory Policies and Procedures information. This MCAI may be found in the
all applicable repairs before further flight, in
(44 FR 11034, February 26, 1979); accordance with the Accomplishment AD docket on the Internet at http://
3. Will not affect intrastate aviation in Instruction of Airbus Service Bulletin A300– www.regulations.gov by searching for and
Alaska; and 53–6184, November 12, 2015, except as locating Docket No. FAA–2016–9051.
4. Will not have a significant required by paragraph (h) of this AD. Repeat (2) For service information identified in
the ultrasonic inspection thereafter at this AD, contact Airbus SAS, Airworthiness
economic impact, positive or negative,
intervals not to exceed 5,400 flight cycles. Office—EAW, 1 Rond Point Maurice
on a substantial number of small entities Bellonte, 31707 Blagnac Cedex, France;
under the criteria of the Regulatory (h) Exceptions to Service Information telephone +33 5 61 93 36 96; fax +33 5 61
Flexibility Act. Specified Paragraph (g) of This AD 93 44 51; email account.airworth-eas@
Where Airbus Service Bulletin A300–53– airbus.com; Internet http://www.airbus.com.
List of Subjects in 14 CFR Part 39 You may view this service information at the
6184, November 12, 2015, specifies to contact
Air transportation, Aircraft, Aviation Airbus for repair instructions, and specifies FAA, Transport Airplane Directorate, 1601
safety, Incorporation by reference, that action as ‘‘RC’’ (Required for Lind Avenue SW., Renton, WA. For
Compliance), this AD requires repair before information on the availability of this
Safety.
further flight using a method approved in material at the FAA, call 425–227–1221.
The Proposed Amendment accordance with the procedures specified in Issued in Renton, Washington, on August
paragraph (i) of this AD. 19, 2016.
Accordingly, under the authority
delegated to me by the Administrator, (i) Other FAA AD Provisions Dorr M. Anderson,
the FAA proposes to amend 14 CFR part The following provisions also apply to this Acting Manager, Transport Airplane
39 as follows: AD: Directorate, Aircraft Certification Service.
(1) Alternative Methods of Compliance [FR Doc. 2016–20685 Filed 8–29–16; 8:45 am]
PART 39—AIRWORTHINESS (AMOCs): The Manager, International Brach, BILLING CODE 4910–13–P
DIRECTIVES FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
■ 1. The authority citation for part 39 14 CFR 39.19, send your request to your DEPARTMENT OF TRANSPORTATION
continues to read as follows: principal inspector or local Flight Standards
District Office, as appropriate. If sending Federal Aviation Administration
Authority: 49 U.S.C. 106(g), 40113, 44701.
information directly to the International
§ 39.13 [Amended] Branch, send it to ATTN: Dan Rodina, 14 CFR Part 39
Aerospace Engineer, International Branch,
mstockstill on DSK3G9T082PROD with PROPOSALS
■ 2. The FAA amends § 39.13 by adding [Docket No. FAA–2016–9050; Directorate
ANM–116, Transport Airplane Directorate,
the following new airworthiness FAA, 1601 Lind Avenue SW., Renton, WA
Identifier 2016–NM–086–AD]
directive (AD): 98057–3356; telephone 425–227–2125; fax RIN 2120–AA64
Airbus: Docket No. FAA–2016–9051; 425–227–1149; email dan.rodina@faa.gov.
Directorate Identifier 2016–NM–035–AD. Information may be emailed to: 9-ANM-116- Airworthiness Directives; The Boeing
AMOC-REQUESTS@faa.gov. Before using Company Airplanes
(a) Comments Due Date any approved AMOC, notify your appropriate
We must receive comments by October 14, principal inspector, or lacking a principal AGENCY:Federal Aviation
2016. inspector, the manager of the local flight Administration (FAA), DOT.
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Costs of Compliance We estimate the following costs to
We estimate that this proposed AD comply with this proposed AD:
affects 53 airplanes of U.S. registry.
ESTIMATED COSTS
Action Labor cost Cost per product Cost on U.S. operators
Inspections and access ................. Up to 815 work-hours × $85 per Up to $69,275 ............................... Up to $3,671,575.
hour = $69,275.
We estimate the following costs to do proposed inspection. We have no way of might need these repairs and on-
any necessary repairs that would be determining the number of aircraft that condition inspections:
required based on the results of the
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Repairs and on-condition inspec- Up to 1,820 work-hours × $85 per N/A ................................................ Up to $154,700.
tions. hour = $154,700.
According to the manufacturer, some For the reasons discussed above, I (b) Affected ADs
of the costs of this proposed AD may be certify this proposed regulation: None.
covered under warranty, thereby (1) Is not a ‘‘significant regulatory
(c) Applicability
reducing the cost impact on affected action’’ under Executive Order 12866,
individuals. We do not control warranty (2) Is not a ‘‘significant rule’’ under This AD applies to The Boeing Company
coverage for affected individuals. As a Model 747–400, –400D, and –400F series
the DOT Regulatory Policies and
result, we have included all costs in our airplanes, certificated in any category, as
Procedures (44 FR 11034, February 26, identified in Boeing Alert Service Bulletin
cost estimate. 1979), 747–53A2878, dated May 19, 2016.
Authority for This Rulemaking (3) Will not affect intrastate aviation
in Alaska, and (d) Subject
Title 49 of the United States Code (4) Will not have a significant Air Transport Association (ATA) of
specifies the FAA’s authority to issue economic impact, positive or negative, America Code 53, Fuselage.
rules on aviation safety. Subtitle I, on a substantial number of small entities
section 106, describes the authority of (e) Unsafe Condition
under the criteria of the Regulatory This AD was prompted by widespread
the FAA Administrator. Subtitle VII: Flexibility Act.
Aviation Programs, describes in more corrosion damage that was found on the skin
detail the scope of the Agency’s List of Subjects in 14 CFR Part 39 inner surface along the upper bulkhead at
certain stations between certain stringers. We
authority. Air transportation, Aircraft, Aviation are issuing this AD to detect and correct
We are issuing this rulemaking under
safety, Incorporation by reference, cracks and corrosion on the crown skin inner
the authority described in Subtitle VII,
Safety. surface. If the cracks or corrosion are not
Part A, Subpart III, Section 44701: repaired, the cracks can rapidly join together
‘‘General requirements.’’ Under that The Proposed Amendment and can cause a sudden decompression and
section, Congress charges the FAA with Accordingly, under the authority loss of structural integrity of the airplane.
promoting safe flight of civil aircraft in delegated to me by the Administrator,
air commerce by prescribing regulations (f) Compliance
the FAA proposes to amend 14 CFR part Comply with this AD within the
for practices, methods, and procedures 39 as follows:
the Administrator finds necessary for compliance times specified, unless already
safety in air commerce. This regulation done.
PART 39—AIRWORTHINESS
is within the scope of that authority DIRECTIVES (g) Inspection of the Skin Inner Surface
because it addresses an unsafe condition At the applicable time specified in
that is likely to exist or develop on ■ 1. The authority citation for part 39 paragraph 1.E., ‘‘Compliance,’’ of Boeing
products identified in this rulemaking continues to read as follows: Alert Service Bulletin 747–53A2878, dated
action. Authority: 49 U.S.C. 106(g), 40113, 44701. May 19, 2016, except as required by
paragraph (k)(1) of this AD: Do a detailed
Regulatory Findings inspection of the skin inner surface for any
§ 39.13 [Amended]
We determined that this proposed AD missing or degraded finish, sign of corrosion,
■ 2. The FAA amends § 39.13 by adding or crack, in accordance with the
would not have federalism implications
mstockstill on DSK3G9T082PROD with PROPOSALS
the following new airworthiness Accomplishment Instructions of Boeing Alert
under Executive Order 13132. This directive (AD):
proposed AD would not have a Service Bulletin 747–53A2878, dated May
The Boeing Company: Docket No. FAA– 19, 2016. Repeat the inspection thereafter at
substantial direct effect on the States, on intervals not to exceed the applicable time
the relationship between the national 2016–9050; Directorate Identifier 2016–
NM–086–AD. specified in paragraph 1.E., ‘‘Compliance,’’ of
Government and the States, or on the Boeing Alert Service Bulletin 747–53A2878,
distribution of power and (a) Comments Due Date dated May 19, 2016, until the actions
responsibilities among the various We must receive comments by October 14, specified in paragraph (i) of this AD have
levels of government. 2016. been done.
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![Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules 59535
(h) Repair of the Skin Inner Surface or lacking a principal inspector, the manager DEPARTMENT OF TRANSPORTATION
If any damage is found during any of the local flight standards district office/
inspection required by paragraph (g) of this certificate holding district office. Federal Aviation Administration
AD, before further flight, do all applicable (3) An AMOC that provides an acceptable
related investigative and correction actions, level of safety may be used for any repair, 14 CFR Part 39
in accordance with the Accomplishment modification, or alteration required by this
Instructions of Boeing Alert Service Bulletin [Docket No. FAA–2016–8849; Directorate
AD if it is approved by the Boeing
747–53A2878, dated May 19, 2016, except as Identifier 2015–NM–174–AD]
Commercial Airplanes Organization
required by paragraph (k)(2) of this AD. RIN 2120–AA64
Designation Authorization (ODA) that has
(i) Terminating Action been authorized by the Manager, Seattle
Modification or repair of the inner skin ACO, to make those findings. To be Airworthiness Directives; Airbus
surfaces in accordance with Part 3 of the approved, the repair method, modification Airplanes
Accomplishment Instructions of Boeing Alert deviation, or alteration deviation must meet AGENCY: Federal Aviation
Service Bulletin 747–53A2878, May 19, 2016, the certification basis of the airplane, and the
terminates the repetitive inspections required
Administration (FAA), DOT.
approval must specifically refer to this AD.
by paragraph (g) of this AD. (4) Except as required by paragraph (k)(1) ACTION: Notice of proposed rulemaking
and (k)(2) of this AD: For service information (NPRM).
(j) Post Repair Inspection and Repairs
that contains steps that are labeled as SUMMARY: We propose to adopt a new
For airplanes on which a repair or
Required for Compliance (RC), the provisions
modification has been done in accordance airworthiness directive (AD) for all
with the Accomplishment Instructions of of paragraphs (l)(4)(i) and (l)(4)(ii) of this AD
Airbus Model A330–223F, –223, –321,
Boeing Alert Service Bulletin 747–53A2878, apply.
–322, and –323 airplanes. The proposed
dated May 19, 2016: Except as required by (i) The steps labeled as RC, including
AD was prompted by fatigue load
paragraph (k)(1) of this AD, at the applicable substeps under an RC step and any figures
analysis that determined the need for
time specified in table 3 of paragraph 1.E., identified in an RC step, must be done to
‘‘Compliance,’’ of Boeing Alert Service certain reduced inspection intervals and
comply with the AD. An AMOC is required
Bulletin 747–53A2878, dated May 19, 2016, updated torque values of the forward
for any deviations to RC steps, including
do detailed inspections to detect damage of substeps and identified figures.
mount pylon bolts. This proposed AD
the repaired or modified areas, and do all (ii) Steps not labeled as RC may be
would require repetitive torque checks
applicable corrective actions, in accordance
deviated from using accepted methods in to determine if there are any loose or
with Part 5 of the Accomplishment broken forward engine mount bolts,
Instructions of Boeing Alert Service Bulletin accordance with the operator’s maintenance
or inspection program without obtaining and, if necessary, replacement of all four
747–53A2878, May 19, 2016, except as forward engine mount bolts and
required by paragraph (k)(2) of this AD. Do approval of an AMOC, provided the RC steps,
including substeps and identified figures, can associated nuts, inspection of the
all applicable corrective actions before
further flight. Repeat the inspections still be done as specified, and the airplane forward mount assembly, and repair.
thereafter at intervals not to exceed the can be put back in an airworthy condition. We are proposing this AD to detect and
applicable time specified in paragraph 1.E., correct loose or broken bolts, which
‘‘Compliance,’’ of Boeing Alert Service (m) Related Information could lead to engine detachment in
Bulletin 747–53A2878, dated May 19, 2016. (1) For more information about this AD, flight, and damage to the airplane.
(k) Exceptions contact Nathan Weigand, Aerospace DATES: We must receive comments on
Engineer, Airframe Branch, ANM–120S, this proposed AD by October 14, 2016.
(1) Where Boeing Alert Service Bulletin
FAA, Seattle ACO, 1601 Lind Avenue SW., ADDRESSES: You may send comments,
747–53A2878, May 19, 2016, specifies a
Renton, WA 98057–3356; phone: 425–917–
compliance time ‘‘after the original issue date using the procedures found in 14 CFR
of this service bulletin,’’ this AD requires 6428; fax: 425–917–6590; email:
11.43 and 11.45, by any of the following
compliance within the specified compliance nathan.p.weigand@faa.gov.
methods:
(2) For service information identified in
time after the effective date of this AD. • Federal eRulemaking Portal: Go to
(2) If any cracking or corrosion is found this AD, contact Boeing Commercial
http://www.regulations.gov. Follow the
during any inspection required by this AD, Airplanes, Attention: Data & Services
and Boeing Alert Service Bulletin 747–
instructions for submitting comments.
Management, P.O. Box 3707, MC 2H–65,
53A2878, May 19, 2016, specifies to contact • Fax: 202–493–2251.
Seattle, WA 98124–2207; telephone 206–
Boeing for appropriate action: Before further • Mail: U.S. Department of
544–5000, extension 1; fax 206–766–5680;
flight, repair the cracking or corrosion using Transportation, Docket Operations, M–
Internet https://www.myboeingfleet.com. You
a method approved in accordance with the 30, West Building Ground Floor, Room
may view this referenced service information
procedures specified in paragraph (l) of this
at the FAA, Transport Airplane Directorate,
W12–140, 1200 New Jersey Avenue SE.,
AD. Washington, DC 20590.
1601 Lind Avenue SW., Renton, WA. For
(l) Alternative Methods of Compliance information on the availability of this
• Hand Delivery: Deliver to Mail
(AMOCs) material at the FAA, call 425–227–1221. address above between 9 a.m. and 5
(1) The Manager, Seattle Aircraft p.m., Monday through Friday, except
Issued in Renton, Washington, on August Federal holidays.
Certification Office (ACO), FAA, has the
18, 2016. For service information identified in
authority to approve AMOCs for this AD, if
requested using the procedures found in 14 Dorr M. Anderson, this NPRM, contact Airbus SAS,
CFR 39.19. In accordance with 14 CFR 39.19, Acting Manager, Transport Airplane Airworthiness Office—EAL, 1 Rond
send your request to your principal inspector Directorate, Aircraft Certification Service. Point Maurice Bellonte, 31707 Blagnac
mstockstill on DSK3G9T082PROD with PROPOSALS
or local Flight Standards District Office, as [FR Doc. 2016–20683 Filed 8–29–16; 8:45 am] Cedex, France; telephone: +33 5 61 93
appropriate. If sending information directly 36 96; fax: +33 5 61 93 45 80; email:
to the manager of the ACO, send it to the BILLING CODE 4910–13–P
airworthiness.A330–A340@airbus.com;
attention of the person identified in
paragraph (m)(1) of this AD. Information may Internet: http://www.airbus.com. You
be emailed to: 9-ANM-Seattle-ACO-AMOC- may view this referenced service
Requests@faa.gov. information at the FAA, Transport
(2) Before using any approved AMOC, Airplane Directorate, 1601 Lind Avenue
notify your appropriate principal inspector, SW., Renton, WA. For information on
VerDate Sep<11>2014 17:56 Aug 29, 2016 Jkt 238001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\30AUP1.SGM 30AUP1](https://thefederalregister.org/doc/81_FR_59700/page/4.svg)
Document Created: 2018-02-09 11:42:47
Document Modified: 2018-02-09 11:42:47
| 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 October 14, 2016. | |
| Contact | Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6428; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 59532 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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