80 FR 32061 - Airworthiness Directives; The Boeing Company Model 757-200 Series Airplanes Modified by Supplemental Type Certificate (STC) ST01529SE or STC ST02278SE
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 108 (June 5, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 108 (June 5, 2015)
| Page Range | 32061-32063 | |
| FR Document | 2015-13358 |
[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)] [Proposed Rules] [Pages 32061-32063] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-13358] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1423; Directorate Identifier 2014-NM-173-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Model 757-200 Series Airplanes Modified by Supplemental Type Certificate (STC) ST01529SE or STC ST02278SE 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 757-200 series airplanes modified by particular STCs. This proposed AD was prompted by reports of a main cargo door being blown past its full open position while on the ground during gusty wind conditions, which resulted in uncontrolled fall down to its closed position. This proposed AD would require installing a new placard and bracket, replacement of an existing placard, and replacement of the main cargo door control panel. We are proposing this AD to prevent damage to the main cargo door, which could result in rapid decompression, leading to in-flight breakup. DATES: We must receive comments on this proposed AD by July 20, 2015. 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 Precision [[Page 32062]] Conversions LLC, 4900 SW Griffith Drive, Suite 133, Beaverton, OR 97005; ATTN: Steven A. Lopez; phone: 503-601-3001; email: [email protected]. 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. 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- 1423; 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: Narinder Luthra, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6513; 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-2015-1423; Directorate Identifier 2014-NM-173-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 reports of a main cargo door being blown past its full open position during gusty wind conditions, resulting in a subsequent uncontrolled fall down to its closed position. It was determined that the Precision Conversions freighter conversion installs a main cargo door that, in certain wind conditions, can rotate open past the full- open position. This can result in damage to the door and surrounding structure, which can go unnoticed by the crew. If a damaged airplane takes off and is pressurized per normal procedures the cargo door could fail. This condition, if not corrected, could result in rapid decompression, leading to in-flight breakup. Related Service Information Under 1 CFR Part 51 We reviewed Precision Conversions LLC Service Bulletin PC-757-11- 0023, dated August 1, 2014. The service information describes procedures for installing a new placard and bracket, replacement of an existing placard, and replacement of the main cargo door control panel. 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 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. Costs of Compliance We estimate that this proposed AD affects 9 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Installation...................... 6 work-hours x $85 per $0 $510 $4,590 hour = $510. ---------------------------------------------------------------------------------------------------------------- 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. [[Page 32063]] 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-2015-1423; Directorate Identifier 2014-NM-173-AD. (a) Comments Due Date We must receive comments by July 20, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 757-200 series airplanes modified by the applicable supplemental type certificate identified in paragraphs (c)(1) and (c)(2) of this AD. (1) ST01529SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/0AF09C3701A237EE86257A5D0064B3AA?OpenDocument&Highlight=st01529se). (2) ST02278SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/E54B5289A2E9F6EF86257B7F0056EDAF?OpenDocument&Highlight=st02278se). (d) Subject Air Transport Association (ATA) of America Code 11, Placards and Markings. (e) Unsafe Condition This AD was prompted by reports of a main cargo door being blown past its full open position while on the ground during gusty wind conditions, which resulted in uncontrolled fall down to its closed position. We are issuing this AD to prevent damage to the main cargo door, which could result in rapid decompression, leading to in- flight breakup. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Installation Within 90 days after the effective date of this AD, install a new placard and bracket, replace the existing placard, and replace the main cargo door control panel, in accordance with the Accomplishment Instructions of Precision Conversions LLC Service Bulletin PC-757-11-0023, dated August 1, 2014. (h) 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 (i)(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. (i) Related Information (1) For more information about this AD, contact Narinder Luthra, Aerospace Engineer, Airframe Branch, ANM 120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6513; fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Precision Conversions LLC, 4900 SW Griffith Drive, Suite 133, Beaverton, OR 97005; ATTN: Steven A. Lopez; phone: 503-601-3001; email: [email protected]. 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 May 18, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-13358 Filed 6-4-15; 8:45 am] BILLING CODE 4910-13-P
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(l) New Requirement of This AD: Repetitive (n) Credit for Previous Actions Issued in Renton, Washington, on May 19,
Inspections for Certain Airplanes This paragraph provides credit for actions 2015.
Repeat the inspection specified in required by paragraphs (i) through (l) of this Dionne Palmero,
paragraph (k) of this AD thereafter at the AD, if those actions were performed before Acting Manager, Transport Airplane
applicable interval specified in paragraphs the effective date of this AD using Airbus Directorate, Aircraft Certification Service.
(l)(1) and (l)(2) of this AD. Service Bulletin A300–57–6044, Revision 03,
dated April 7, 1999, including Appendix 01, [FR Doc. 2015–13335 Filed 6–4–15; 8:45 am]
(1) For airplanes whose flight time average
is equal to or more than 1.5 hours, at which is not incorporated by reference in this BILLING CODE 4910–13–P
intervals not to exceed 8,500 flight cycles or AD.
18,500 flight hours, whichever occurs first.
(o) Exception to Service Information
(2) For airplanes whose flight time average DEPARTMENT OF TRANSPORTATION
is less than 1.5 hours, at intervals not to Specification
exceed 9,200 flight cycles or 13,700 flight Although Airbus Service Bulletin A300– Federal Aviation Administration
hours, whichever occurs first. 57–6044, Revision 04, including Appendix
01, dated August 19, 2011, specifies to 14 CFR Part 39
(m) New Requirement of This AD: Corrective submit information to Airbus, this AD does
Actions not require that submission. [Docket No. FAA–2015–1423; Directorate
(1) If any cracking is detected or suspected Identifier 2014–NM–173–AD]
(p) Other FAA AD Provisions
during any detailed visual inspection
required by paragraph (i) or (j) of this AD: The following provisions also apply to this RIN 2120–AA64
Before further flight, confirm this finding and AD:
the length of this cracking by conducting an (1) Alternative Methods of Compliance Airworthiness Directives; The Boeing
HFEC inspection, in accordance with the (AMOCs): The Manager, International Company Model 757–200 Series
Accomplishment Instructions of Airbus Branch, ANM–116, Transport Airplane Airplanes Modified by Supplemental
Service Bulletin A300–57–6044, Revision 04, Directorate, FAA, has the authority to Type Certificate (STC) ST01529SE or
including Appendix 01, dated August 19, approve AMOCs for this AD, if requested STC ST02278SE
2011, except as specified in paragraph (o) of using the procedures found in 14 CFR 39.19.
this AD. If no cracking is confirmed during In accordance with 14 CFR 39.19, send your AGENCY: Federal Aviation
the HFEC inspection, accomplish the request to your principal inspector or local Administration (FAA), DOT.
applicable repetitive inspections required by Flight Standards District Office, as ACTION: Notice of proposed rulemaking
paragraphs (j) and (l) of this AD at the appropriate. If sending information directly
to the International Branch, send it to ATTN:
(NPRM).
applicable time specified in those
paragraphs. Dan Rodina, Aerospace Engineer, SUMMARY: We propose to adopt a new
(2) If any cracking is found during any International Branch, ANM–116, Transport
airworthiness directive (AD) for certain
HFEC inspection required by paragraph (i), Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356; The Boeing Company Model 757–200
(j), (k) or (l) of this AD: Before further flight,
do the applicable actions specified in telephone 425–227–2125; fax 425–227–1149. series airplanes modified by particular
paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. Information may be emailed to: 9-ANM-116- STCs. This proposed AD was prompted
(i) If the cracking is 75 mm or less per each AMOC-REQUESTS@faa.gov. Before using by reports of a main cargo door being
rib bay: Before further flight, repair the any approved AMOC, notify your appropriate blown past its full open position while
cracking, in accordance with the principal inspector, or lacking a principal on the ground during gusty wind
Accomplishment Instructions of Airbus inspector, the manager of the local flight conditions, which resulted in
Service Bulletin A300–57–6044, Revision 04, standards district office/certificate holding
uncontrolled fall down to its closed
including Appendix 01, dated August 19, district office. The AMOC approval letter
must specifically reference this AD. position. This proposed AD would
2011, except as specified in paragraph (o) of
this AD. Do repetitive detailed visual (2) Contacting the Manufacturer: As of the require installing a new placard and
inspections of the repaired area thereafter at effective date of this AD, for any requirement bracket, replacement of an existing
intervals not to exceed 50 flight cycles or 110 in this AD to obtain corrective actions from placard, and replacement of the main
flight hours, whichever occurs first, in a manufacturer, the action must be cargo door control panel. We are
accordance with the Accomplishment accomplished using a method approved by proposing this AD to prevent damage to
Instructions of Airbus Service Bulletin A300– the Manager, International Branch, ANM– the main cargo door, which could result
57–6044, Revision 04, including Appendix 116, Transport Airplane Directorate, FAA; or in rapid decompression, leading to in-
01, dated August 19, 2011. Within 250 flight EASA; or Airbus’s EASA DOA. If approved
cycles or 550 flight hours, whichever occurs by the DOA, the approval must include the
flight breakup.
first after doing the temporary repair, do a DOA-authorized signature. DATES: We must receive comments on
permanent repair of the repaired area, in this proposed AD by July 20, 2015.
accordance with the Accomplishment (q) Related Information
ADDRESSES: You may send comments,
Instructions of Airbus Service Bulletin A300– (1) Refer to Mandatory Continuing using the procedures found in 14 CFR
57–6044, Revision 04, including Appendix Airworthiness Information (MCAI) EASA
11.43 and 11.45, by any of the following
01, dated August 19, 2011. Airworthiness Directive 2013–0221, dated
(ii) If the cracking exceeds 75 mm per any September 19, 2013, for related information. methods:
rib bay: Before further flight, install Airbus This MCAI may be found in the AD docket • Federal eRulemaking Portal: Go to
Modification 10089, in accordance with the on the Internet at http://www.regulations.gov http://www.regulations.gov. Follow the
Accomplishment Instructions of Airbus by searching for and locating Docket No. instructions for submitting comments.
Service Bulletin A300–57–6044, Revision 04, FAA–2015–1426. • Fax: 202–493–2251.
including Appendix 01, dated August 19, (2) For service information identified in • Mail: U.S. Department of
2011. Do an LFEC inspection thereafter at the this AD, contact Airbus SAS, Airworthiness Transportation, Docket Operations, M–
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
intervals specified in paragraph (l) of this Office—EAW, 1 Rond Point Maurice 30, West Building Ground Floor, Room
AD. Bellonte, 31707 Blagnac Cedex, France; W12–140, 1200 New Jersey Avenue SE.,
(3) If any cracking is found during any telephone +33 5 61 93 36 96; fax +33 5 61
Washington, DC 20590.
inspection required by this AD at fastener 93 44 51; email account.airworth-eas@
• Hand Delivery: Deliver to Mail
holes 1A, 1, or 2: Before further flight, repair airbus.com; Internet http://www.airbus.com.
the cracking, in accordance with the You may view this service information at the address above between 9 a.m. and 5
Accomplishment Instructions of Airbus FAA, Transport Airplane Directorate, 1601 p.m., Monday through Friday, except
Service Bulletin A300–57–6044, Revision 04, Lind Avenue SW., Renton, WA. For Federal holidays.
including Appendix 01, dated August 19, information on the availability of this For service information identified in
2011. material at the FAA, call 425–227–1221. this proposed AD, contact Precision
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![Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32063
List of Subjects in 14 CFR Part 39 Precision Conversions LLC Service Bulletin requires repetitive inspections to detect
PC–757–11–0023, dated August 1, 2014. fatigue cracking of the front spar vertical
Air transportation, Aircraft, Aviation
safety, Incorporation by reference, (h) Alternative Methods of Compliance stringers on the wings; and repair, if
Safety. (AMOCs) necessary. Since we issued AD 98–18–
(1) The Manager, Seattle Aircraft 26, we have received reports that
The Proposed Amendment Certification Office (ACO), FAA, has the indicate new repetitive inspections
Accordingly, under the authority authority to approve AMOCs for this AD, if having new thresholds and intervals are
delegated to me by the Administrator, requested using the procedures found in 14 needed and that additional work is
the FAA proposes to amend 14 CFR part CFR 39.19. In accordance with 14 CFR 39.19, needed to accomplish the inspections
send your request to your principal inspector on airplanes on which a previous
39 as follows:
or local Flight Standards District Office, as modification has been accomplished.
appropriate. If sending information directly
PART 39—AIRWORTHINESS to the manager of the ACO, send it to the This proposed AD would require
DIRECTIVES attention of the person identified in repetitive high frequency eddy current
paragraph (i)(1) of this AD. Information may (HFEC) inspections for cracking of the
■ 1. The authority citation for part 39 be emailed to: 9-ANM-Seattle-ACO-AMOC- radius of the front spar vertical stringers
continues to read as follows: Requests@faa.gov. and the horizontal floor beam on frame
Authority: 49 U.S.C. 106(g), 40113, 44701. (2) Before using any approved AMOC, 36, and a rototest inspection for
notify your appropriate principal inspector, cracking of the fastener holes of the
§ 39.13 [Amended] or lacking a principal inspector, the manager front spar vertical stringers on frame 36,
■ 2. The FAA amends § 39.13 by adding of the local flight standards district office/
certificate holding district office. and repair if necessary. We are
the following new airworthiness proposing this AD to detect and correct
directive (AD): (i) Related Information fatigue cracking of the front spar vertical
The Boeing Company: Docket No. FAA– (1) For more information about this AD, stringers on the wings, which could
2015–1423; Directorate Identifier 2014– contact Narinder Luthra, Aerospace Engineer, result in the reduced structural integrity
NM–173–AD. Airframe Branch, ANM 120S, FAA, Seattle of the airframe.
Aircraft Certification Office (ACO), 1601 Lind
(a) Comments Due Date Avenue SW., Renton, WA 98057–3356; DATES: We must receive comments on
We must receive comments by July 20, phone: 425–917–6513; fax: 425–917–6590; this proposed AD by July 20, 2015.
2015. email: Narinder.Luthra@faa.gov. ADDRESSES: You may send comments by
(2) For service information identified in any of the following methods:
(b) Affected ADs this AD, contact Precision Conversions LLC, • Federal eRulemaking Portal: Go to
None. 4900 SW Griffith Drive, Suite 133, Beaverton, http://www.regulations.gov. Follow the
OR 97005; ATTN: Steven A. Lopez; phone:
(c) Applicability
503–601–3001; email: Steven.Lopez@
instructions for submitting comments.
This AD applies to The Boeing Company precisionaircraft.com. You may view this • Fax: 202–493–2251.
Model 757–200 series airplanes modified by referenced service information at the FAA, • Mail: U.S. Department of
the applicable supplemental type certificate Transport Airplane Directorate, 1601 Lind Transportation, Docket Operations, M–
identified in paragraphs (c)(1) and (c)(2) of Avenue SW., Renton, WA. For information 30, West Building Ground Floor, Room
this AD. on the availability of this material at the W12–140, 1200 New Jersey Avenue SE.,
(1) ST01529SE (http://rgl.faa.gov/ FAA, call 425–227–1221. Washington, DC 20590.
Regulatory_and_Guidance_Library/rgstc.nsf/
Issued in Renton, Washington, on May 18, • Hand Delivery: U.S. Department of
0/0AF09C3701A237EE86257A5D0064B3AA?
OpenDocument&Highlight=st01529se). 2015. Transportation, Docket Operations, M–
(2) ST02278SE (http://rgl.faa.gov/ John P. Piccola, Jr., 30, West Building Ground Floor, Room
Regulatory_and_Guidance_Library/rgstc.nsf/ Acting Manager, Transport Airplane W12–140, 1200 New Jersey Avenue SE.,
0/E54B5289A2E9F6EF86257B7F0056EDAF? Directorate, Aircraft Certification Service. Washington, DC, between 9 a.m. and 5
OpenDocument&Highlight=st02278se). [FR Doc. 2015–13358 Filed 6–4–15; 8:45 am] p.m., Monday through Friday, except
(d) Subject BILLING CODE 4910–13–P
Federal holidays.
For service information identified in
Air Transport Association (ATA) of
this proposed AD, contact Airbus,
America Code 11, Placards and Markings.
DEPARTMENT OF TRANSPORTATION Airworthiness Office—EIAS, 1 Rond
(e) Unsafe Condition Point Maurice Bellonte, 31707 Blagnac
This AD was prompted by reports of a Federal Aviation Administration Cedex, France; telephone +33 5 61 93 36
main cargo door being blown past its full 96; fax +33 5 61 93 44 51; email
open position while on the ground during 14 CFR Part 39 account.airworth-eas@airbus.com;
gusty wind conditions, which resulted in Internet http://www.airbus.com. You
uncontrolled fall down to its closed position. [Docket No. FAA–2015–1422; Directorate
Identifier 2014–NM–125–AD] may view this referenced service
We are issuing this AD to prevent damage to
information at the FAA, Transport
the main cargo door, which could result in RIN 2120–AA64
rapid decompression, leading to in-flight Airplane Directorate, 1601 Lind Avenue
breakup. SW., Renton, WA. For information on
Airworthiness Directives; Airbus the availability of this material at the
(f) Compliance Airplanes FAA, call 425–227–1221.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Comply with this AD within the AGENCY: Federal Aviation
compliance times specified, unless already Examining the AD Docket
Administration (FAA), DOT.
done. You may examine the AD docket on
ACTION: Notice of proposed rulemaking
(g) Installation (NPRM). the Internet at http://
Within 90 days after the effective date of
www.regulations.gov by searching for
this AD, install a new placard and bracket, SUMMARY: We propose to supersede and locating Docket No. FAA–2015–
replace the existing placard, and replace the Airworthiness Directive (AD) 98–18–26, 1422; or in person at the Docket
main cargo door control panel, in accordance for certain Airbus Model A320 series Management Facility between 9 a.m.
with the Accomplishment Instructions of airplanes. AD 98–18–26 currently and 5 p.m., Monday through Friday,
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Document Created: 2015-12-15 15:20:50
Document Modified: 2015-12-15 15:20:50
| 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 July 20, 2015. | |
| Contact | Narinder Luthra, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6513; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 32061 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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