81 FR 41894 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 124 (June 28, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 124 (June 28, 2016)
| Page Range | 41894-41897 | |
| FR Document | 2016-14966 |
[Federal Register Volume 81, Number 124 (Tuesday, June 28, 2016)] [Proposed Rules] [Pages 41894-41897] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-14966] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7270; Directorate Identifier 2015-NM-116-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 737-700 and -700C series airplanes. This proposed AD was prompted by a report that for airplanes with blended winglets, the nose-up pitch trim limit and associated warning for the horizontal stabilizer control system will allow take-off with incorrect trim settings. This proposed AD would require, depending on airplane configuration, replacing the pitch trim light plates on the flight deck control stand, relocating the position warning horn switches of the horizontal stabilizer, revising the software, removing the placard, and doing related investigative and corrective actions if necessary. We are proposing this AD to prevent take-off with incorrect settings of the horizontal stabilizer pitch trim system. Settings outside of the appropriate pitch trim limits could result in loss of controllability of the airplane during take-off. DATES: We must receive comments on this proposed AD by August 12, 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 Aviation Partners Boeing service information identified in this NPRM, contact Aviation Partners Boeing, 2811 South 102nd Street, Suite 200, Seattle, WA 98168; phone: 206-830-7699; fax: 206-767-3355; email: [email protected]; Internet: http://www.aviationpartnersboeing.com. [[Page 41895]] For The Boeing Company 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. Boeing Alert Service Bulletin 737-27A1306, dated September 10, 2015, is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 7270. 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- 7270; 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: Fnu Winarto, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6659; 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-2016-7270; Directorate Identifier 2015-NM-116-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 that for airplanes with blended winglets, the nose-up pitch trim limit and associated warning for the horizontal stabilizer control system will allow takeoff with incorrect trim settings. The trim control system was recently analyzed for potential nose-up mis-trim occurrences during take-off for airplanes with blended winglets. Results of the analysis indicated that Model 737-700 airplanes with blended winglets are not compliant with the certification rules for specific conditions. This condition, if not corrected, could result in the loss of controllability of the airplane during take-off. Related Service Information Under 1 CFR Part 51 We reviewed Aviation Partners Boeing Service Bulletin AP737-27-002, Revision 2, dated March 1, 2016, and Boeing Alert Service Bulletin 737- 27A1306, dated September 10, 2015. The service information describes procedures for replacing the pitch trim light plates on the flight deck control stand, relocating the position warning horn switches of the horizontal stabilizer, revising the software, and doing related investigative and corrective actions. The related investigative actions include verifying that the stabilizer ``B'' measurement is at a certain dimension, performing a light plate function test, performing a stabilizer functional test, loading and verifying model/engine database software, performing a flight management computer configuration check, and verifying all settings. The corrective actions include adjusting the stabilizer, adjusting the light plate, replacing the light plate, rigging and adjusting the horizontal stabilizer trim system, and repairing the light plate switch. We reviewed Aviation Partners Service Bulletin AP737-34-005, dated July 17, 2015. The service information describes procedures for revising the software and removing the placard. 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 Boeing Alert Service Bulletin 737-27A1306, dated September 10, 2015, at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-7270. Differences Between This Proposed AD and the Service Information The service information specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 569 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 ---------------------------------------------------------------------------------------------------------------- Relocation..................... Up to 4 work-hours x $0 Up to $340........ Up to $193,460 $85 per hour = $340. Replacement.................... Up to 3 work-hours x $1,973 Up to $2,228...... Up to $1,267,732 $85 per hour = $255. Software installation.......... 2 work-hours x $85 per 0 170............... 96,730 hour = $170. [[Page 41896]] Placard Removal (2 airplanes).. 1 work-hour x $85 per 0 85................ 170 hour = $85. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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-2016-7270; Directorate Identifier 2015-NM-116-AD. (a) Comments Due Date We must receive comments by August 12, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 737-700 and -700C series airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category. (1) Airplanes having supplemental type certificate ST00830SE installed (Aviation Partners Boeing blended winglets), as identified in Aviation Partners Boeing Service Bulletin AP737-27-002, Revision 2, dated March 1, 2016. (2) Airplanes identified in Boeing Alert Service Bulletin 737- 27A1306, dated September 10, 2015. (3) Airplanes identified in Aviation Partners Service Bulletin AP737-34-005, dated July 17, 2015. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls. (e) Unsafe Condition This AD was prompted by a report that for airplanes with blended winglets, the nose-up pitch trim limit and associated warning for the horizontal stabilizer control system will allow take-off with incorrect trim settings. We are issuing this AD to prevent take-off with incorrect settings of the horizontal stabilizer pitch trim system. Settings outside of the appropriate pitch trim limits could result in loss of controllability of the airplane during take-off. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement, Relocation, and Applicable Related Investigative and Corrective Actions (1) For airplanes identified in paragraph (c)(1) of this AD: Within 72 months after the effective date of this AD, relocate the position warning horn switches of the horizontal stabilizer, replace the pitch trim light plates on the flight deck control stand, revise the software, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP737-27- 002, Revision 2, dated March 1, 2016; except as specified in paragraph (j) of this AD. Do all applicable related investigative and corrective actions before further flight. (2) For airplanes identified in paragraph (c)(2) of this AD: Within 72 months after the effective date of this AD, relocate the position warning horn switches of the horizontal stabilizer, replace the pitch trim light plates on the flight deck control stand, revise the software, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1306, dated September 10, 2015, and Aviation Partners Boeing Service Bulletin AP737-27-002, Revision 2, dated March 1, 2016; except as specified in paragraph (j) of this AD. Do all applicable related investigative and corrective actions before further flight. (h) Software Revision and Placard Removal For airplanes identified in paragraph (c)(3) of this AD: Within 72 months after the effective date of this AD, revise the software and remove the placard, in accordance with the Accomplishment Instructions of Aviation Partners Service Bulletin AP737-34-005, dated July 17, 2015. (i) Credit for Actions Accomplished in Accordance With Previous Service Information This paragraph provides credit for the actions specified in paragraphs (g)(1) and (g)(2) of this AD, if those actions were performed before the effective date of this AD using Aviation Partners Boeing Service Bulletin AP737-27-002, dated March 31, 2015; or Aviation Partners Boeing Service Bulletin AP737-27-002, Revision 1, dated August 6, 2015. [[Page 41897]] (j) Exception to the Service Information Where Aviation Partners Boeing Service Bulletin AP737-27-002, Revision 2, dated March 1, 2016, specifies to contact Boeing for appropriate action, and specifies that action as Required for Compliance (RC): Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair, 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 (j) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) 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. (l) Related Information (1) For more information about this AD, contact Fnu Winarto, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6659; fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Aviation Partners Boeing, 2811 South 102nd Street, Suite 200, Seattle, WA 98168; phone: 206-830-7699; fax: 206-767-3355; email: [email protected]; Internet: http://www.aviationpartnersboeing.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 June 14, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-14966 Filed 6-27-16; 8:45 am] BILLING CODE 4910-13-P
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(d) Subject Airplane Directorate, FAA; or EASA; or DEPARTMENT OF TRANSPORTATION
Air Transport Association (ATA) of Airbus’s EASA Design Organization
America Code 53, Fuselage. Approval (DOA). Federal Aviation Administration
(e) Reason (k) Other FAA AD Provisions
14 CFR Part 39
This AD was prompted by a report The following provisions also apply to this
indicating that during inspections to detect AD: [Docket No. FAA–2016–7270; Directorate
corrosion of the bulk cargo doors, several (1) Alternative Methods of Compliance Identifier 2015–NM–116–AD]
cracks were discovered. We are issuing this (AMOCs): The Manager, International RIN 2120–AA64
AD to detect and correct cracking of the bulk Branch, ANM–116, Transport Airplane
cargo doors; such cracking could result in
rapid airplane decompression or possible Directorate, FAA, has the authority to Airworthiness Directives; The Boeing
loss of the bulk cargo door. approve AMOCs for this AD, if requested Company Airplanes
using the procedures found in 14 CFR 39.19.
(f) Compliance In accordance with 14 CFR 39.19, send your
AGENCY: Federal Aviation
Comply with this AD within the request to your principal inspector or local Administration (FAA), DOT.
compliance times specified, unless already Flight Standards District Office, as ACTION: Notice of proposed rulemaking
done. appropriate. If sending information directly (NPRM).
(g) Inspection to the International Branch, send it to ATTN:
SUMMARY: We propose to adopt a new
Dan Rodina, Aerospace Engineer,
Within 250 flight cycles or 6 months after airworthiness directive (AD) for certain
the effective date of this AD, whichever International Branch, ANM–116, Transport
The Boeing Company Model 737–700
occurs first, do a general visual inspection of Airplane Directorate, FAA, 1601 Lind
and –700C series airplanes. This
the bulk cargo door frame to identify the Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149.
proposed AD was prompted by a report
existence of any structural repairs, in
Information may be emailed to: 9-ANM-116-
that for airplanes with blended winglets,
accordance with the instructions of Airbus
Alert Operators Transmission (AOT) AMOC-REQUESTS@faa.gov. Before using the nose-up pitch trim limit and
A53W010–15, Revision 00, including any approved AMOC, notify your appropriate associated warning for the horizontal
Appendixes 1, 2, and 3, dated December 15, principal inspector, or lacking a principal stabilizer control system will allow take-
2015. inspector, the manager of the local flight off with incorrect trim settings. This
standards district office/certificate holding proposed AD would require, depending
(h) Detailed Visual Inspection
district office. The AMOC approval letter on airplane configuration, replacing the
If, during the general visual inspection pitch trim light plates on the flight deck
required in paragraph (g) of this AD, any must specifically reference this AD.
(2) Contacting the Manufacturer: For any control stand, relocating the position
repair is found on the bulk cargo door frame:
Before further flight, do a detailed visual requirement in this AD to obtain corrective warning horn switches of the horizontal
inspection for cracking of the frame at the actions from a manufacturer, the action must stabilizer, revising the software,
repaired area, in accordance with the be accomplished using a method approved removing the placard, and doing related
instructions of Airbus AOT A53W010–15, by the Manager, International Branch, ANM– investigative and corrective actions if
Revision 00, including Appendixes 1, 2, and 116, Transport Airplane Directorate, FAA; or necessary. We are proposing this AD to
3, dated December 15, 2015. the EASA; or Airbus’s EASA Design prevent take-off with incorrect settings
(i) Crack Repair Organization Approval (DOA). If approved by of the horizontal stabilizer pitch trim
the DOA, the approval must include the system. Settings outside of the
If any cracking is found during the detailed
visual inspection required by paragraph (h) DOA-authorized signature. appropriate pitch trim limits could
of this AD: Before further flight, repair using result in loss of controllability of the
(l) Related Information
a method approved by the Manager, airplane during take-off.
International Branch, ANM–116, Transport (1) Refer to Mandatory Continuing DATES: We must receive comments on
Airplane Directorate, FAA; or EASA; or Airworthiness Information (MCAI) EASA
this proposed AD by August 12, 2016.
Airbus’s EASA Design Organization Airworthiness Directive 2015–0238, dated
ADDRESSES: You may send comments,
Approval (DOA). December 18, 2015, for related information.
This MCAI may be found in the AD docket using the procedures found in 14 CFR
(j) Post-Repair Actions for Crack-Free 11.43 and 11.45, by any of the following
on the Internet at http://www.regulations.gov
Frames methods:
by searching for and locating Docket No.
If no cracking is found during the detailed FAA–2016–7269. • Federal eRulemaking Portal: Go to
visual inspection required by paragraph (h) (2) For service information identified in http://www.regulations.gov. Follow the
of this AD: Do the actions in paragraphs (j)(1) this AD, contact Airbus SAS, Airworthiness instructions for submitting comments.
and (j)(2) of this AD.
Office—EAW, 1 Rond Point Maurice • Fax: 202–493–2251.
(1) At the applicable time specified in
Bellonte, 31707 Blagnac Cedex, France; • Mail: U.S. Department of
paragraph (j)(1)(i) or (j)(1)(ii) of this AD: Send Transportation, Docket Operations, M–
a report of the inspection results to Airbus telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@ 30, West Building Ground Floor, Room
Service Bulletin Reporting Online
Application on Airbus World (https:// airbus.com; Internet http://www.airbus.com. W12–140, 1200 New Jersey Avenue SE.,
w3.airbus.com/). You may view this service information at the Washington, DC 20590.
(i) If the inspection was done on or after FAA, Transport Airplane Directorate, 1601 • Hand Delivery: Deliver to Mail
the effective date of this AD: Submit the Lind Avenue SW., Renton, WA. For address above between 9 a.m. and 5
report within 60 days after the inspection. p.m., Monday through Friday, except
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
information on the availability of this
(ii) If the inspection was done before the material at the FAA, call 425–227–1221. Federal holidays.
effective date of this AD: Submit the report For Aviation Partners Boeing service
within 60 days after the effective date of this Issued in Renton, Washington, on June 10,
information identified in this NPRM,
AD. 2016.
contact Aviation Partners Boeing, 2811
(2) Within 2,800 flight cycles after the Michael Kaszycki,
detailed visual inspection required by
South 102nd Street, Suite 200, Seattle,
Acting Manager, Transport Airplane WA 98168; phone: 206–830–7699; fax:
paragraph (h) of this AD: Do applicable post- Directorate, Aircraft Certification Service.
repair inspections and repairs, using a 206–767–3355; email: leng@
method approved by the Manager, [FR Doc. 2016–14968 Filed 6–27–16; 8:45 am] aviationpartners.com; Internet: http://
International Branch, ANM–116, Transport BILLING CODE 4910–13–P www.aviationpartnersboeing.com.
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ESTIMATED COSTS—Continued
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Placard Removal (2 air- 1 work-hour × $85 per hour = $85 ......................... 0 85 ........................... 170
planes).
We have received no definitive data on a substantial number of small entities We are issuing this AD to prevent take-off
that would enable us to provide cost under the criteria of the Regulatory with incorrect settings of the horizontal
estimates for the on-condition actions Flexibility Act. stabilizer pitch trim system. Settings outside
of the appropriate pitch trim limits could
specified in this proposed AD.
According to the manufacturer, some List of Subjects in 14 CFR Part 39 result in loss of controllability of the airplane
during take-off.
of the costs of this proposed AD may be Air transportation, Aircraft, Aviation
covered under warranty, thereby safety, Incorporation by reference, (f) Compliance
reducing the cost impact on affected Safety. Comply with this AD within the
individuals. We do not control warranty compliance times specified, unless already
The Proposed Amendment done.
coverage for affected individuals. As a
result, we have included all costs in our Accordingly, under the authority (g) Replacement, Relocation, and Applicable
cost estimate. delegated to me by the Administrator, Related Investigative and Corrective Actions
the FAA proposes to amend 14 CFR part
Authority for This Rulemaking (1) For airplanes identified in paragraph
39 as follows: (c)(1) of this AD: Within 72 months after the
Title 49 of the United States Code effective date of this AD, relocate the position
specifies the FAA’s authority to issue PART 39—AIRWORTHINESS warning horn switches of the horizontal
rules on aviation safety. Subtitle I, DIRECTIVES stabilizer, replace the pitch trim light plates
section 106, describes the authority of on the flight deck control stand, revise the
■ 1. The authority citation for part 39 software, and do all applicable related
the FAA Administrator. Subtitle VII:
continues to read as follows: investigative and corrective actions, in
Aviation Programs, describes in more
Authority: 49 U.S.C. 106(g), 40113, 44701. accordance with the Accomplishment
detail the scope of the Agency’s Instructions of Aviation Partners Boeing
authority. § 39.13 [Amended] Service Bulletin AP737–27–002, Revision 2,
We are issuing this rulemaking under dated March 1, 2016; except as specified in
the authority described in Subtitle VII, ■ 2. The FAA amends § 39.13 by adding
paragraph (j) of this AD. Do all applicable
Part A, Subpart III, Section 44701: the following new airworthiness
related investigative and corrective actions
‘‘General requirements.’’ Under that directive (AD): before further flight.
section, Congress charges the FAA with The Boeing Company: Docket No. FAA– (2) For airplanes identified in paragraph
promoting safe flight of civil aircraft in 2016–7270; Directorate Identifier 2015– (c)(2) of this AD: Within 72 months after the
NM–116–AD. effective date of this AD, relocate the position
air commerce by prescribing regulations
warning horn switches of the horizontal
for practices, methods, and procedures (a) Comments Due Date stabilizer, replace the pitch trim light plates
the Administrator finds necessary for We must receive comments by August 12, on the flight deck control stand, revise the
safety in air commerce. This regulation 2016. software, and do all applicable related
is within the scope of that authority investigative and corrective actions, in
(b) Affected ADs
because it addresses an unsafe condition accordance with the Accomplishment
that is likely to exist or develop on None. Instructions of Boeing Alert Service Bulletin
products identified in this rulemaking 737–27A1306, dated September 10, 2015,
(c) Applicability
and Aviation Partners Boeing Service
action. This AD applies to The Boeing Company Bulletin AP737–27–002, Revision 2, dated
Regulatory Findings Model 737–700 and –700C series airplanes March 1, 2016; except as specified in
identified in paragraphs (c)(1), (c)(2), and paragraph (j) of this AD. Do all applicable
We determined that this proposed AD (c)(3) of this AD, certificated in any category. related investigative and corrective actions
would not have federalism implications (1) Airplanes having supplemental type before further flight.
under Executive Order 13132. This certificate ST00830SE installed (Aviation
Partners Boeing blended winglets), as (h) Software Revision and Placard Removal
proposed AD would not have a
substantial direct effect on the States, on identified in Aviation Partners Boeing For airplanes identified in paragraph (c)(3)
the relationship between the national Service Bulletin AP737–27–002, Revision 2, of this AD: Within 72 months after the
dated March 1, 2016. effective date of this AD, revise the software
Government and the States, or on the
(2) Airplanes identified in Boeing Alert and remove the placard, in accordance with
distribution of power and Service Bulletin 737–27A1306, dated the Accomplishment Instructions of Aviation
responsibilities among the various September 10, 2015. Partners Service Bulletin AP737–34–005,
levels of government. (3) Airplanes identified in Aviation dated July 17, 2015.
For the reasons discussed above, I Partners Service Bulletin AP737–34–005, (i) Credit for Actions Accomplished in
certify this proposed regulation: dated July 17, 2015. Accordance With Previous Service
(1) Is not a ‘‘significant regulatory
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(d) Subject Information
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under Air Transport Association (ATA) of This paragraph provides credit for the
America Code 27, Flight controls. actions specified in paragraphs (g)(1) and
the DOT Regulatory Policies and
(g)(2) of this AD, if those actions were
Procedures (44 FR 11034, February 26, (e) Unsafe Condition performed before the effective date of this AD
1979), This AD was prompted by a report that for using Aviation Partners Boeing Service
(3) Will not affect intrastate aviation airplanes with blended winglets, the nose-up Bulletin AP737–27–002, dated March 31,
in Alaska, and pitch trim limit and associated warning for 2015; or Aviation Partners Boeing Service
(4) Will not have a significant the horizontal stabilizer control system will Bulletin AP737–27–002, Revision 1, dated
economic impact, positive or negative, allow take-off with incorrect trim settings. August 6, 2015.
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(j) Exception to the Service Information 767–3355; email: leng@aviationpartners.com; • Mail: U.S. Department of
Where Aviation Partners Boeing Service Internet: http:// Transportation, Docket Operations, M–
Bulletin AP737–27–002, Revision 2, dated www.aviationpartnersboeing.com. You may 30, West Building Ground Floor, Room
March 1, 2016, specifies to contact Boeing for view this referenced service information at
the FAA, Transport Airplane Directorate,
W12–140, 1200 New Jersey Avenue SE.,
appropriate action, and specifies that action Washington, DC 20590.
as Required for Compliance (RC): Before 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this • Hand Delivery: Deliver to Mail
further flight, repair using a method
approved in accordance with the procedures material at the FAA, call 425–227–1221. address above between 9 a.m. and 5
specified in paragraph (k) of this AD. Issued in Renton, Washington, on June 14,
p.m., Monday through Friday, except
2016. Federal holidays.
(k) Alternative Methods of Compliance For service information identified in
(AMOCs) Dionne Palermo,
this NPRM, contact Bombardier, Inc., Q-
(1) The Manager, Seattle Aircraft Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
Series Technical Help Desk, 123 Garratt
Certification office (ACO), FAA, has the Boulevard, Toronto, Ontario M3K 1Y5,
authority to approve AMOCs for this AD, if [FR Doc. 2016–14966 Filed 6–27–16; 8:45 am]
Canada; telephone: 416–375–4000; fax:
requested using the procedures found in 14 BILLING CODE 4910–13–P
CFR 39.19. In accordance with 14 CFR 39.19, 416–375–4539; email: thd.qseries@
send your request to your principal inspector aero.bombardier.com; Internet: http://
or local Flight Standards District Office, as www.bombardier.com. You may view
DEPARTMENT OF TRANSPORTATION
appropriate. If sending information directly this referenced service information at
to the manager of the ACO, send it to the Federal Aviation Administration the FAA, Transport Airplane
attention of the person identified in Directorate, 1601 Lind Avenue SW.,
paragraph (l)(1) of this AD. Information may Renton, WA. For information on the
be emailed to: 9-ANM-Seattle-ACO-AMOC- 14 CFR Part 39
availability of this material at the FAA,
Requests@faa.gov. [Docket No. FAA–2016–7267; Directorate
(2) Before using any approved AMOC, call 425–227–1221.
Identifier 2016–NM–015–AD]
notify your appropriate principal inspector, Examining the AD Docket
or lacking a principal inspector, the manager RIN 2120–AA64
of the local flight standards district office/ You may examine the AD docket on
certificate holding district office. Airworthiness Directives; Bombardier, the Internet at http://
(3) An AMOC that provides an acceptable Inc. Airplanes www.regulations.gov by searching for
level of safety may be used for any repair, and locating Docket No. FAA–2016–
modification, or alteration required by this AGENCY: Federal Aviation
7267; or in person at the Docket
AD if it is approved by the Boeing Administration (FAA), DOT.
Management Facility between 9 a.m.
Commercial Airplanes Organization ACTION: Notice of proposed rulemaking
Designation Authorization (ODA) that has and 5 p.m., Monday through Friday,
(NPRM). except Federal holidays. The AD docket
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair SUMMARY: We propose to adopt a new contains this proposed AD, the
method to be approved, the repair, airworthiness directive (AD) for certain regulatory evaluation, any comments
modification deviation, or alteration Bombardier, Inc. Model DHC–8–102, received, and other information. The
deviation must meet the certification basis of –103, and –106 airplanes, Model DHC– street address for the Docket Operations
the airplane, and the approval must office (telephone: 800–647–5527) is in
8–200 series airplanes, and Model DHC–
specifically refer to this AD. the ADDRESSES section. Comments will
(4) Except as required by paragraph (j) of 8–300 series airplanes. This proposed
AD was prompted by several be available in the AD docket shortly
this AD: For service information that
contains steps that are labeled as Required occurrences of loss of airspeed data on after receipt.
for Compliance (RC), the provisions of both pilot and co-pilot air speed FOR FURTHER INFORMATION CONTACT:
paragraphs (k)(4)(i) and (k)(4)(ii) of this AD indicators due to the accumulation of Assata Dessaline, Aerospace Engineer,
apply. ice on the pitot probes. An investigation Avionics and Services Branch, ANE–
(i) The steps labeled as RC, including revealed that the accumulation of ice 172, FAA, New York Aircraft
substeps under an RC step and any figures was due to inoperative pitot probe Certification Office (ACO), 1600 Stewart
identified in an RC step, must be done to
heaters. This proposed AD would Avenue, Suite 410, Westbury, NY
comply with the AD. An AMOC is required
for any deviations to RC steps, including require replacing the existing circuit 11590; telephone: 516–228–7301; fax:
substeps and identified figures. breakers in both the left and right side 516–794–5531.
(ii) Steps not labeled as RC may be of the pitot heater system with circuit SUPPLEMENTARY INFORMATION:
deviated from using accepted methods in breakers that have higher trip points.
accordance with the operator’s maintenance We are proposing this AD to prevent Comments Invited
or inspection program without obtaining circuit breakers from tripping and We invite you to send any written
approval of an AMOC, provided the RC steps, cutting power supply to the pitot probe relevant data, views, or arguments about
including substeps and identified figures, can heater, which could cause loss of this proposed AD. Send your comments
still be done as specified, and the airplane
airspeed data and result in the to an address listed under the
can be put back in an airworthy condition.
flightcrew not being able to control the ADDRESSES section. Include ‘‘Docket No.
(l) Related Information airspeed of the airplane. FAA–2016–7267; Directorate Identifier
(1) For more information about this AD, DATES: We must receive comments on 2016–NM–015–AD’’ at the beginning of
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
contact Fnu Winarto, Aerospace Engineer, this proposed AD by August 12, 2016. your comments. We specifically invite
Systems and Equipment Branch, ANM–130S, ADDRESSES: You may send comments, comments on the overall regulatory,
FAA, Seattle Aircraft Certification Office economic, environmental, and energy
(ACO), 1601 Lind Avenue SW., Renton, WA
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following aspects of this proposed AD. We will
98057–3356; phone: 425–917–6659; fax: 425–
917–6590; email: fnu.winarto@faa.gov. methods: consider all comments received by the
(2) For service information identified in • Federal eRulemaking Portal: Go to closing date and may amend this
this AD, contact Aviation Partners Boeing, http://www.regulations.gov. Follow the proposed AD based on those comments.
2811 South 102nd Street, Suite 200, Seattle, instructions for submitting comments. We will post all comments we
WA 98168; phone: 206–830–7699; fax: 206– • Fax: 202–493–2251. receive, without change, to http://
VerDate Sep<11>2014 16:20 Jun 27, 2016 Jkt 238001 PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 E:\FR\FM\28JNP1.SGM 28JNP1](https://thefederalregister.org/doc/81_FR_42018/page/4.svg)
Document Created: 2016-06-28 00:53:38
Document Modified: 2016-06-28 00:53:38
| 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 12, 2016. | |
| Contact | Fnu Winarto, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6659; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 41894 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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