81 FR 40205 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 119 (June 21, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 119 (June 21, 2016)
| Page Range | 40205-40208 | |
| FR Document | 2016-14293 |
[Federal Register Volume 81, Number 119 (Tuesday, June 21, 2016)] [Proposed Rules] [Pages 40205-40208] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-14293] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7261; Directorate Identifier 2016-NM-004-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 747-200B, 747-300, 747-400, 747-400D, and 747-400F series airplanes. This proposed AD was prompted by a report of cracking in both the aluminum strut side skin, and corrosion resistant steel (CRES) outer spring beam support fitting. This proposed AD would require repetitive high frequency eddy current (HFEC) inspections for cracking in the strut side skin; an open-hole HFEC inspection for cracking, applicable related investigative and corrective actions; and a fastener installation modification. We are proposing this AD to detect and correct cracking of the strut side skin; such cracking could result in the failure of the outer spring beam support fitting, which could cause separation of a strut and engine from the airplane during flight. DATES: We must receive comments on this proposed AD by August 5, 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. [[Page 40206]] 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-2016-7261. 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- 7261; 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-2016-7261; Directorate Identifier 2016-NM-004-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 a report indicating cracking in both the aluminum strut side skin, and CRES outer spring beam support fitting. This condition, if not corrected, could result in the failure of the outer spring beam support fitting, which could cause separation of a strut and engine from the airplane during flight. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015. The service information describes procedures for repetitive high HFEC inspections for cracking in the strut side skin, an open-hole HFEC inspection for cracking, applicable related investigative and corrective actions, and a fastener installation modification. 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 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-2016-7261. 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 This Proposed AD and the Service Information Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015, 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. Costs of Compliance We estimate that this proposed AD affects 320 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 ---------------------------------------------------------------------------------------------------------------- Inspection............... 291 work-hours x $85 per $0 $24,735 per $7,915,200 per hour = $24,735 per inspection cycle. inspection cycle. inspection cycle. Modification............. Up to 490 work-hours x 56,414 Up to $98,064....... Up to $31,380,480. $85 per hour = $41,650. ---------------------------------------------------------------------------------------------------------------- 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, [[Page 40207]] 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-2016-7261; Directorate Identifier 2016-NM-004-AD. (a) Comments Due Date We must receive comments by August 5, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747-200B, 747-300, 747-400, 747-400D, and 747-400F series airplanes, certificated in any category, equipped with General Electric (GE) CF6-80 series engines or Pratt & Whitney PW4000 series engines; as identified in Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015. (d) Subject Air Transport Association (ATA) of America Code 54; Nacelles/ pylons. (e) Unsafe Condition This AD was prompted by a report of cracking in both the aluminum strut side skin, and corrosion resistant steel (CRES) outer spring beam support fitting. We are issuing this AD to detect and correct cracking of the strut side skin; such cracking could result in the failure of the outer spring beam support fitting, which could cause separation of a strut and engine from the airplane during flight. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Except as provided by paragraph (i)(1) and (i)(2) of this AD, at the applicable compliance time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015, do a surface high frequency eddy current (HFEC) inspection for cracking of the strut side skin, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015, except as required by paragraph (i)(3) of this AD. Repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015, until the actions required by paragraph (h) of this AD are done. If any cracking is found, do the actions specified in paragraph (h) of this AD. (h) Terminating Actions Within the applicable compliance time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015, except as provided by paragraphs (i)(1) and (i)(2) of this AD: Do a fastener hole open-hole HFEC inspection for cracking, applicable related investigative and corrective actions, and a fastener installation modification, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 54A2245, dated December 18, 2015, except as required by paragraph (i)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Doing the actions required by this paragraph terminates the repetitive inspections required by paragraph (g) of this AD. (i) Exceptions to Service Information (1) Where Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015, 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) The Condition column in table 1 and table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015, refers to total flight cycles ``at the original issue date of this service bulletin.'' This AD, however, applies to the airplanes with the specified total flight cycles as of the effective date of this AD. (3) Although Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015, specifies to contact Boeing for repair instructions, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (j) 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 (k)(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 (i)(3) of this AD, for service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(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 [[Page 40208]] still be done as specified, and the airplane can be put back in an airworthy condition. (k) Related Information (1) For more information about this AD, 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]. (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, 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 June 3, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-14293 Filed 6-20-16; 8:45 am] BILLING CODE 4910-13-P
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Regulatory Findings hydraulic module plate and subsequent loss Issued in Fort Worth, Texas, on June 9,
of control of the helicopter. 2016.
We determined that this proposed AD
(c) Comments Due Date Scott A. Horn,
would not have federalism implications
under Executive Order 13132. This Acting Manager, Rotorcraft Directorate,
We must receive comments by August 22,
Aircraft Certification Service.
proposed AD would not have a 2016.
[FR Doc. 2016–14470 Filed 6–20–16; 8:45 am]
substantial direct effect on the States, on (d) Compliance
the relationship between the national BILLING CODE 4910–13–P
Government and the States, or on the You are responsible for performing each
action required by this AD within the
distribution of power and
specified compliance time unless it has DEPARTMENT OF TRANSPORTATION
responsibilities among the various already been accomplished prior to that time.
levels of government. Federal Aviation Administration
For the reasons discussed, I certify (e) Required Actions
this proposed regulation: (1) Within 100 hours time-in-service (TIS): 14 CFR Part 39
1. Is not a ‘‘significant regulatory (i) Visually inspect the split pins,
action’’ under Executive Order 12866; castellated nuts, plugs, nuts, and hexagon [Docket No. FAA–2016–7261; Directorate
2. Is not a ‘‘significant rule’’ under the bolts of each attachment point for a crack and Identifier 2016–NM–004–AD]
DOT Regulatory Policies and Procedures for proper installation by following the
RIN 2120–AA64
(44 FR 11034, February 26, 1979); Accomplishment Instructions, paragraphs
3. Will not affect intrastate aviation in 3.B.1.2.a. through 3.B.1.2.e., of Airbus Airworthiness Directives; The Boeing
Helicopters Alert Service Bulletin (ASB) No.
Alaska to the extent that it justifies Company Airplanes
ASB MBB–BK117 C–2–29A–003, Revision 0,
making a regulatory distinction; and dated October 12, 2015 (ASB MBB–BK117 C–
4. Will not have a significant AGENCY: Federal Aviation
2–29A–003), or Airbus Helicopters ASB No. Administration (FAA), DOT.
economic impact, positive or negative, ASB MBB–BK117 D–2–29A–001, Revision 0,
on a substantial number of small entities ACTION: Notice of proposed rulemaking
dated October 12, 2015 (ASB MBB–BK117 D–
under the criteria of the Regulatory 2–29A–001), as applicable to your model (NPRM).
Flexibility Act. helicopter. Replace any part that has a crack
SUMMARY: We propose to adopt a new
We prepared an economic evaluation before further flight. If the split pins,
castellated nuts, or hexagon bolts are not as airworthiness directive (AD) for certain
of the estimated costs to comply with
depicted in Figure 2 of ASB MBB–BK117 C– The Boeing Company Model 747–200B,
this proposed AD and placed it in the
2–29A–003 or ASB MBB–BK117 D–2–29A– 747–300, 747–400, 747–400D, and 747–
AD docket.
001, before further flight, properly install 400F series airplanes. This proposed AD
List of Subjects in 14 CFR Part 39 them. was prompted by a report of cracking in
Air transportation, Aircraft, Aviation (ii) Apply a torque of 9 to 10 Nm to the both the aluminum strut side skin, and
left-hand and right-hand nuts of each corrosion resistant steel (CRES) outer
safety, Incorporation by reference, attachment point. If a torque of 9 to 10 Nm
Safety. spring beam support fitting. This
cannot be applied, replace the affected nut proposed AD would require repetitive
The Proposed Amendment before further flight. high frequency eddy current (HFEC)
(2) Thereafter, at intervals not to exceed
Accordingly, under the authority inspections for cracking in the strut side
400 hours TIS, perform the inspection in
delegated to me by the Administrator, paragraph (e)(1)(i) of this AD.
skin; an open-hole HFEC inspection for
the FAA proposes to amend 14 CFR part cracking, applicable related
(f) Alternative Methods of Compliance investigative and corrective actions; and
39 as follows:
(AMOCs) a fastener installation modification. We
PART 39—AIRWORTHINESS (1) The Manager, Safety Management are proposing this AD to detect and
DIRECTIVES Group, FAA, may approve AMOCs for this correct cracking of the strut side skin;
AD. Send your proposal to: Matt Fuller, such cracking could result in the failure
■ 1. The authority citation for part 39 Senior Aviation Safety Engineer, Safety of the outer spring beam support fitting,
continues to read as follows: Management Group, Rotorcraft Directorate, which could cause separation of a strut
FAA, 10101 Hillwood Pkwy., Fort Worth, TX
Authority: 49 U.S.C. 106(g), 40113, 44701. and engine from the airplane during
76177; telephone (817) 222–5110; email 9-
ASW-FTW-AMOC-Requests@faa.gov.
flight.
§ 39.13 [Amended]
(2) For operations conducted under a 14 DATES: We must receive comments on
■ 2. The FAA amends § 39.13 by adding CFR part 119 operating certificate or under this proposed AD by August 5, 2016.
the following new airworthiness 14 CFR part 91, subpart K, we suggest that ADDRESSES: You may send comments,
directive (AD): you notify your principal inspector, or
using the procedures found in 14 CFR
Airbus Helicopters Deutschland GmbH: lacking a principal inspector, the manager of
the local flight standards district office or 11.43 and 11.45, by any of the following
Docket No. FAA–2016–7415; Directorate methods:
Identifier 2015–SW–076–AD. certificate holding district office before
operating any aircraft complying with this • Federal eRulemaking Portal: Go to
(a) Applicability AD through an AMOC. http://www.regulations.gov. Follow the
This AD applies to Model MBB–BK 117 C– instructions for submitting comments.
(g) Additional Information • Fax: 202–493–2251.
2 and MBB–BK 117 D–2 helicopters with a
hydraulic module plate assembly part The subject of this AD is addressed in • Mail: U.S. Department of
rmajette on DSK2TPTVN1PROD with PROPOSALS
number B291M0003103 with a single locking European Aviation Safety Agency (EASA) AD Transportation, Docket Operations, M–
attachment point installed, certificated in any No. 2015–0210R1, Revision 1, dated October 30, West Building Ground Floor, Room
category. 28, 2015. You may view the EASA AD on the W12–140, 1200 New Jersey Avenue SE.,
Internet at http://www.regulations.gov in the
(b) Unsafe Condition Washington, DC 20590.
AD Docket.
This AD defines the unsafe condition as • Hand Delivery: Deliver to Mail
failure of a hydraulic module plate assembly (h) Subject address above between 9 a.m. and 5
attachment point (attachment point). This Joint Aircraft Service Component (JASC) p.m., Monday through Friday, except
condition could result in loss of the Code: 2900, Hydraulic Power System. Federal holidays.
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Part A, Subpart III, Section 44701: (b) Affected ADs (i) Exceptions to Service Information
‘‘General requirements.’’ Under that None. (1) Where Boeing Alert Service Bulletin
section, Congress charges the FAA with 747–54A2245, dated December 18, 2015,
(c) Applicability specifies a compliance time ‘‘after the
promoting safe flight of civil aircraft in
air commerce by prescribing regulations This AD applies to The Boeing Company original issue date of this service bulletin,’’
for practices, methods, and procedures Model 747–200B, 747–300, 747–400, 747– this AD requires compliance within the
400D, and 747–400F series airplanes, specified compliance time after the effective
the Administrator finds necessary for
certificated in any category, equipped with date of this AD.
safety in air commerce. This regulation (2) The Condition column in table 1 and
General Electric (GE) CF6–80 series engines
is within the scope of that authority or Pratt & Whitney PW4000 series engines; as table 2 of paragraph 1.E., ‘‘Compliance,’’ of
because it addresses an unsafe condition identified in Boeing Alert Service Bulletin Boeing Alert Service Bulletin 747–54A2245,
that is likely to exist or develop on 747–54A2245, dated December 18, 2015. dated December 18, 2015, refers to total flight
products identified in this rulemaking cycles ‘‘at the original issue date of this
action. (d) Subject service bulletin.’’ This AD, however, applies
Air Transport Association (ATA) of to the airplanes with the specified total flight
Regulatory Findings America Code 54; Nacelles/pylons. cycles as of the effective date of this AD.
We determined that this proposed AD (3) Although Boeing Alert Service Bulletin
(e) Unsafe Condition 747–54A2245, dated December 18, 2015,
would not have federalism implications specifies to contact Boeing for repair
under Executive Order 13132. This This AD was prompted by a report of
cracking in both the aluminum strut side instructions, and specifies that action as
proposed AD would not have a ‘‘RC’’ (Required for Compliance), this AD
skin, and corrosion resistant steel (CRES)
substantial direct effect on the States, on requires repair before further flight using a
outer spring beam support fitting. We are
the relationship between the national method approved in accordance with the
issuing this AD to detect and correct cracking
Government and the States, or on the procedures specified in paragraph (j) of this
of the strut side skin; such cracking could AD.
distribution of power and result in the failure of the outer spring beam
responsibilities among the various support fitting, which could cause separation (j) Alternative Methods of Compliance
levels of government. of a strut and engine from the airplane during (AMOCs)
For the reasons discussed above, I flight. (1) The Manager, Seattle Aircraft
certify this proposed regulation: Certification Office (ACO), FAA, has the
(1) Is not a ‘‘significant regulatory (f) Compliance
authority to approve AMOCs for this AD, if
action’’ under Executive Order 12866, Comply with this AD within the requested using the procedures found in 14
(2) Is not a ‘‘significant rule’’ under compliance times specified, unless already CFR 39.19. In accordance with 14 CFR 39.19,
the DOT Regulatory Policies and done. send your request to your principal inspector
Procedures (44 FR 11034, February 26, or local Flight Standards District Office, as
(g) Repetitive Inspections appropriate. If sending information directly
1979),
(3) Will not affect intrastate aviation Except as provided by paragraph (i)(1) and to the manager of the ACO, send it to the
(i)(2) of this AD, at the applicable compliance attention of the person identified in
in Alaska, and
time specified in paragraph 1.E., paragraph (k)(1) of this AD. Information may
(4) Will not have a significant be emailed to: 9-ANM-Seattle-ACO-AMOC-
‘‘Compliance,’’ of Boeing Alert Service
economic impact, positive or negative, Bulletin 747–54A2245, dated December 18, Requests@faa.gov.
on a substantial number of small entities 2015, do a surface high frequency eddy (2) Before using any approved AMOC,
under the criteria of the Regulatory current (HFEC) inspection for cracking of the notify your appropriate principal inspector,
Flexibility Act. strut side skin, in accordance with the or lacking a principal inspector, the manager
Accomplishment Instructions of Boeing Alert of the local flight standards district office/
List of Subjects in 14 CFR Part 39 certificate holding district office.
Service Bulletin 747–54A2245, dated
Air transportation, Aircraft, Aviation December 18, 2015, except as required by (3) An AMOC that provides an acceptable
safety, Incorporation by reference, paragraph (i)(3) of this AD. Repeat the level of safety may be used for any repair,
Safety. inspection thereafter at the applicable times modification, or alteration required by this
AD if it is approved by the Boeing
specified in paragraph 1.E., ‘‘Compliance,’’ of
The Proposed Amendment Boeing Alert Service Bulletin 747–54A2245,
Commercial Airplanes Organization
Designation Authorization (ODA) that has
Accordingly, under the authority dated December 18, 2015, until the actions
been authorized by the Manager, Seattle
delegated to me by the Administrator, required by paragraph (h) of this AD are
ACO, to make those findings. To be
the FAA proposes to amend 14 CFR part done. If any cracking is found, do the actions approved, the repair method, modification
39 as follows: specified in paragraph (h) of this AD. deviation, or alteration deviation must meet
(h) Terminating Actions the certification basis of the airplane, and the
PART 39—AIRWORTHINESS approval must specifically refer to this AD.
DIRECTIVES Within the applicable compliance time (4) Except as required by paragraph (i)(3)
specified in paragraph 1.E., ‘‘Compliance,’’ of of this AD, for service information that
■ 1. The authority citation for part 39 Boeing Alert Service Bulletin 747–54A2245, contains steps that are labeled as Required
continues to read as follows: dated December 18, 2015, except as provided for Compliance (RC), the provisions of
by paragraphs (i)(1) and (i)(2) of this AD: Do paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
Authority: 49 U.S.C. 106(g), 40113, 44701. a fastener hole open-hole HFEC inspection apply.
§ 39.13 [Amended] for cracking, applicable related investigative (i) The steps labeled as RC, including
and corrective actions, and a fastener substeps under an RC step and any figures
■ 2. The FAA amends § 39.13 by adding installation modification, in accordance with identified in an RC step, must be done to
the following new airworthiness
rmajette on DSK2TPTVN1PROD with PROPOSALS
the Accomplishment Instructions of Boeing comply with the AD. An AMOC is required
directive (AD): Alert Service Bulletin 747–54A2245, dated for any deviations to RC steps, including
The Boeing Company: Docket No. FAA– December 18, 2015, except as required by substeps and identified figures.
2016–7261; Directorate Identifier 2016– paragraph (i)(3) of this AD. Do all applicable (ii) Steps not labeled as RC may be
NM–004–AD. related investigative and corrective actions deviated from using accepted methods in
before further flight. Doing the actions accordance with the operator’s maintenance
(a) Comments Due Date required by this paragraph terminates the or inspection program without obtaining
We must receive comments by August 5, repetitive inspections required by paragraph approval of an AMOC, provided the RC steps,
2016. (g) of this AD. including substeps and identified figures, can
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still be done as specified, and the airplane ADDRESSES: You may send comments, section. Include ‘‘Docket No. FAA–
can be put back in an airworthy condition. using the procedures found in 14 CFR 2016–6901; Directorate Identifier 2015–
(k) Related Information 11.43 and 11.45, by any of the following NM–192–AD’’ at the beginning of your
(1) For more information about this AD,
methods: comments. We specifically invite
contact Nathan Weigand, Aerospace • Federal eRulemaking Portal: Go to comments on the overall regulatory,
Engineer, Airframe Branch, ANM–120S, http://www.regulations.gov. Follow the economic, environmental, and energy
FAA, Seattle Aircraft Certification Office instructions for submitting comments. aspects of this proposed AD. We will
(ACO), 1601 Lind Avenue SW., Renton, WA • Fax: 202–493–2251. consider all comments received by the
98057–3356; phone: 425–917–6428; fax: 425– • Mail: U.S. Department of closing date and may amend this
917–6590; email: nathan.p.weigand@faa.gov. Transportation, Docket Operations, M– proposed AD because of those
(2) For service information identified in 30, West Building Ground Floor, Room comments.
this AD, contact Boeing Commercial W12–140, 1200 New Jersey Avenue SE., We will post all comments we
Airplanes, Attention: Data & Services receive, without change, to http://
Washington, DC 20590.
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
• Hand Delivery: Deliver to Mail www.regulations.gov, including any
544–5000, extension 1; fax 206–766–5680; address above between 9 a.m. and 5 personal information you provide. We
Internet https://www.myboeingfleet.com. You p.m., Monday through Friday, except will also post a report summarizing each
may view this referenced service information Federal holidays. substantive verbal contact we receive
at the FAA, the FAA, Transport Airplane For service information identified in about this proposed AD.
Directorate, 1601 Lind Avenue SW., Renton, this NPRM, contact Boeing Commercial Discussion
WA. For information on the availability of Airplanes, Attention: Data & Services
this material at the FAA, call 425–227–1221. Management, P.O. Box 3707, MC 2H–65, Fatigue damage can occur locally, in
Issued in Renton, Washington, on June 3, Seattle, WA 98124–2207; telephone small areas or structural design details,
2016. 206–544–5000, extension 1; fax 206– or globally, in widespread areas.
Michael Kaszycki, 766–5680; Internet https:// Multiple-site damage is widespread
www.myboeingfleet.com. You may view damage that occurs in a large structural
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service. this referenced service information at element such as a single rivet line of a
the FAA, Transport Airplane lap splice joining two large skin panels.
[FR Doc. 2016–14293 Filed 6–20–16; 8:45 am]
Directorate, 1601 Lind Avenue SW., Widespread damage can also occur in
BILLING CODE 4910–13–P
Renton, WA. For information on the multiple elements such as adjacent
availability of this material at the FAA, frames or stringers. Multiple-site
call 425–227–1221. It is also available damage and multiple-element damage
DEPARTMENT OF TRANSPORTATION
on the Internet at http:// cracks are typically too small initially to
Federal Aviation Administration www.regulations.gov by searching for be reliably detected with normal
and locating Docket No. FAA–2016– inspection methods. Without
14 CFR Part 39 intervention, these cracks will grow,
6901.
and eventually compromise the
[Docket No. FAA–2016–6901; Directorate Examining the AD Docket structural integrity of the airplane. This
Identifier 2015–NM–192–AD] condition is known as widespread
You may examine the AD docket on
RIN 2120–AA64 the Internet at http:// fatigue damage. It is associated with
www.regulations.gov by searching for general degradation of large areas of
Airworthiness Directives; The Boeing and locating Docket No. FAA–2016– structure with similar structural details
Company Airplanes 6901; or in person at the Docket and stress levels. As an airplane ages,
Management Facility between 9 a.m. WFD will likely occur, and will
AGENCY: Federal Aviation certainly occur if the airplane is
Administration (FAA), DOT. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket operated long enough without any
ACTION: Notice of proposed rulemaking intervention.
contains this proposed AD, the
(NPRM). The FAA’s WFD final rule (75 FR
regulatory evaluation, any comments
69746, November 15, 2010) became
SUMMARY: We propose to adopt a new received, and other information. The
effective on January 14, 2011. The WFD
airworthiness directive (AD) for certain street address for the Docket Office
rule requires certain actions to prevent
The Boeing Company Model 737–600, (phone: 800–647–5527) is in the
structural failure due to WFD
–700, –700C, –800, and –900 series ADDRESSES section. Comments will be
throughout the operational life of
airplanes. This proposed AD was available in the AD docket shortly after
certain existing transport category
prompted by an evaluation by the receipt.
airplanes and all of these airplanes that
design approval holder (DAH) FOR FURTHER INFORMATION CONTACT: will be certificated in the future. For
indicating that the aft pressure bulkhead Alan Pohl, Aerospace Engineer, existing and future airplanes subject to
is subject to widespread fatigue damage Airframe Branch, ANM–120S, FAA, the WFD rule, the rule requires that
(WFD). This proposed AD would Seattle Aircraft Certification Office DAHs establish a limit of validity (LOV)
require repetitive inspections of the aft (ACO), 1601 Lind Avenue SW., Renton, of the engineering data that support the
pressure bulkhead web for any cracking, WA 98057–3356; phone: 425–917–6450; structural maintenance program.
crack indications, discrepant fastener fax: 425–917–6590; email: Alan.Pohl@ Operators affected by the WFD rule may
rmajette on DSK2TPTVN1PROD with PROPOSALS
holes, and corrosion; and corrective faa.gov. not fly an airplane beyond its LOV,
actions if necessary. We are proposing SUPPLEMENTARY INFORMATION: unless an extended LOV is approved.
this AD to detect and correct cracks in The WFD rule (75 FR 69746,
the aft pressure bulkhead web, which Comments Invited November 15, 2010) does not require
could result in an uncontrolled We invite you to send any written identifying and developing maintenance
decompression of the fuselage. relevant data, views, or arguments about actions if the DAHs can show that such
DATES: We must receive comments on this proposal. Send your comments to actions are not necessary to prevent
this proposed AD by August 5, 2016. an address listed under the ADDRESSES WFD before the airplane reaches the
VerDate Sep<11>2014 14:42 Jun 20, 2016 Jkt 238001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\21JNP1.SGM 21JNP1](https://thefederalregister.org/doc/81_FR_40324/page/4.svg)
Document Created: 2016-06-21 01:30:42
Document Modified: 2016-06-21 01:30:42
| 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 August 5, 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 40205 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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