81 FR 24012 - Airworthiness Directives; Kaman Aerospace Corporation
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 79 (April 25, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 79 (April 25, 2016)
| Page Range | 24012-24014 | |
| FR Document | 2016-09434 |
[Federal Register Volume 81, Number 79 (Monday, April 25, 2016)] [Rules and Regulations] [Pages 24012-24014] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-09434] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-0183; Directorate Identifier 2015-SW-016- AD;Amendment 39-18498; AD 2016-08-21] RIN 2120-AA64 Airworthiness Directives; Kaman Aerospace Corporation AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for Kaman Aerospace Corporation (Kaman) Model K-1200 helicopters. This AD requires revising the ``Flight Limitations--NO LOAD'' and ``Flight Limitations-- [[Page 24013]] LOAD'' sections of the rotorcraft flight manual (RFM). This AD was prompted by a report of certain flight maneuvers that may lead to main rotor (M/R) blade to opposing hub contact. These actions are intended to prevent damage to the M/R flight controls and subsequent loss of control of the helicopter. DATES: This AD is effective May 31, 2016. ADDRESSES: For service information identified in this final rule, contact Kaman Aerospace Corporation, Old Windsor Rd., P.O. Box 2, Bloomfield, Connecticut 06002-0002; telephone (860) 242-4461; fax (860) 243-7047; or at http://www.kamanaero.com. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. 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- 0183; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800-647-5527) is U.S. Department of Transportation, Docket Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7190; email [email protected]. SUPPLEMENTARY INFORMATION: Discussion On January 21, 2016, at 81 FR 3344, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Kaman Model K-1200 helicopters. The NPRM proposed to require revising the ``Flight Limitations-NO LOAD'' and ``Flight Limitations-LOAD'' sections of the RFM by inserting a warning and limitations about rearward to forward flight, establishing maximum rearward and sideward flight speeds, and prohibiting weather-vanning takeoffs and departures to turn the helicopter. The NPRM was prompted by a report of a Model K-1200 helicopter turning suddenly and causing blade contact with the hub. The report suggests that a rapid aircraft yaw rate and subsequent yaw arresting maneuver may cause low clearance of the M/R blades with the opposing M/R hub. This condition could cause an M/R blade to strike the opposing rotor's flight controls. The proposed requirements were intended to prevent damage to the M/R flight controls and subsequent loss of control of the helicopter. The NPRM published with the previous mailing address for the Boston Aircraft Certification Office. We have revised this contact information in this final rule to reflect the new mailing address. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (81 FR 3344, January 21, 2016). FAA's Determination We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of the same type design and that air safety and the public interest require adopting the AD requirements as proposed. Related Service Information Kaman has issued Kaman K-1200 RFM, Revision 5, dated April 14, 2015. This revision of the limitations section of the RFM inserts, for both load operations and no load operations, a warning and limitations about departing from rearward to forward flight, a maximum rearward flight speed of 25 knots, a maximum sideward flight speed of 17 knots, and a prohibition on weather-vanning takeoffs and departures as a method to turn aircraft. Costs of Compliance We estimate that this AD will affect 16 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per work- hour, we expect revising the RFM will require 0.5 work-hour, for cost of about $43 per helicopter, or $688 for the U.S. fleet. 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 This AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866; (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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): 2016-08-21 Kaman Aerospace Corporation (Kaman): Amendment 39-18498; Docket [[Page 24014]] No. FAA-2016-0183; Directorate Identifier 2015-SW-016-AD. (a) Applicability This AD applies to Model K-1200 helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a main rotor (M/R) blade striking the opposing rotor's flight controls. This condition could result in damage to the M/R flight controls and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective May 31, 2016. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions Within 10 hours time-in-service, revise Section 2 Limitations of the Kaman K-1200 Rotorcraft Flight Manual (RFM) by inserting a copy of this AD into the RFM or by making pen-and-ink changes, as follows: (1) In the ``Flight Limitations--NO LOAD'' and ``Flight Limitations--WITH LOAD'' sections, add the information in Figure 1 to paragraph (e)(1) of this AD. [GRAPHIC] [TIFF OMITTED] TR25AP16.011 (2) In the ``Flight Limitations--NO LOAD'' and ``Flight Limitations--WITH LOAD'' sections, add the following: Maximum rearward flight speed: 25 knots. Maximum sideward flight speed: 17 knots. Weather-vanning takeoffs/departures as a method to turn aircraft: Prohibited. (f) Credit for Actions Previously Completed Incorporating the changes contained in Kaman K-1200 RFM, Revision 5, dated April 14, 2015, before the effective date of this AD is considered acceptable for compliance with the corresponding actions specified in paragraph (e) of this AD. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7190; email [email protected]. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (h) Additional Information Kaman K-1200 RFM, Revision 5, dated April 14, 2015, which is not incorporated by reference, contains additional information about the subject of this final rule. For service information identified in this final rule, contact Kaman Aerospace Corporation, Old Windsor Rd., P.O. Box 2, Bloomfield, Connecticut 06002-0002; telephone (860) 242-4461; fax (860) 243-7047; or at http://www.kamanaero.com. You may review a copy of this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. (i) Subject Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor Control. Issued in Fort Worth, Texas, on April 15, 2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016-09434 Filed 4-22-16; 8:45 am] BILLING CODE 4910-13-P
![24012 Federal Register / Vol. 81, No. 79 / Monday, April 25, 2016 / Rules and Regulations
(e) Compliance actuator with servo actuator P/N 222–382– (j) Subject
You are responsible for performing each 001–111 or P/N 222–382–001–111FM. Joint Aircraft Service Component (JASC)
action required by this AD within the (5) Inspect the portion of the piston rod for Code: 6730, Rotorcraft Servo System.
specified compliance time unless it has any absence of cadmium plating (bare base
already been accomplished prior to that time. metal), as shown in Figure 7 of the (k) Material Incorporated by Reference
Woodward ASB. If there is any bare base (1) The Director of the Federal Register
(f) Required Actions metal on the piston rod in this area, apply approved the incorporation by reference
Before further flight: brush cadmium plating to all bare and (IBR) of the service information listed in this
(1) Disassemble each servo actuator to gain reworked areas using SPS5070 or equivalent paragraph under 5 U.S.C. 552(a) and 1 CFR
access to the piston rod as shown in Figures 0.0002 to 0.0005 inch thick and rework the part 51.
1 through 5 and by following the piston rod by following the Accomplishment (2) You must use this service information
Accomplishment Instructions, paragraph Instructions, paragraph C., Part III, C.1.1.1. as applicable to do the actions required by
3.A., Part I., of Woodward HRT Alert Service through C.1.1.3., of the Woodward ASB. this AD, unless the AD specifies otherwise.
Bulletin No. 141600–67–02, dated August 18, (6) Reassemble the servo actuator by (3) The following service information was
2010 (Woodward ASB). following the Accomplishment Instructions, approved for IBR on December 9, 2010 (75 FR
(2) Clean the entire piston rod and nut paragraph C, Part III, 1.1.4. through 3.3.4. of
71540, November 24, 2010).
using acetone and a nylon bristle brush the Woodward ASB.
(i) Woodward HRT Alert Service Bulletin
removing all contaminates to allow for (g) Credit for Actions Previously Completed No. 141600–67–02, dated August 18, 2010.
inspection. Inspect the grind relief (ii) Reserved.
configuration for the piston rod and nut as Compliance with the Woodward ASB or
with AD 2010–19–51 (75 FR 71540, (4) For Woodward HRT service information
shown in Figure 6 of the Woodward ASB. If identified in this AD, contact Bell Helicopter
the grind relief is unacceptable as shown in November 24, 2010) before the effective date
of this AD is considered acceptable for Textron Canada Limited, 12,800 Rue de
Figure 6, replace the piston rod and the nut l’Avenir, Mirabel, Quebec J7J1R4; telephone
with airworthy parts. compliance with the corresponding
inspections specified in paragraph (f) of this (450) 437–2862 or (800) 363–8023; fax (450)
(3) Using a 10X or higher magnifying glass, 433–0272; or at http://
visually inspect the nut for any corrosion or AD. If you replaced the piston rod pursuant
to the Woodward ASB or paragraph (d)(1) or www.bellcustomer.com/files/.
any damage to the threads. If you find any (5) You may view this service information
corrosion or any damage to the threads, (d)(3) of AD 2010–19–51, apply the
requirements of paragraph (f)(4)(iv) of this at FAA, Office of the Regional Counsel,
replace the nut with an airworthy nut. Southwest Region, 10101 Hillwood Pkwy.,
(4) Using a 10X or higher magnifying glass, AD.
Room 6N–321, Fort Worth, TX 76177. For
visually inspect the piston rod as shown in (h) Alternative Methods of Compliance information on the availability of this
Figure 7 of the Woodward ASB for any (AMOCs) material at the FAA, call (817) 222–5110.
corrosion, visible lack of cadmium plate (6) You may view this service information
(1) The Manager, Safety Management
(gold or gray color), or damage to the piston that is incorporated by reference at the
Group, FAA, may approve AMOCs for this
rod. For the purposes of this AD, damage to National Archives and Records
AD. Send your proposal to: Matt Wilbanks,
the piston rod is defined as pitting, a visible Administration (NARA). For information on
Aviation Safety Engineer, Regulations and
scratch, a crack, or a visible abrasion. the availability of this material at NARA, call
Policy Group, Rotorcraft Directorate, FAA,
(i) If there is any corrosion or visible lack (202) 741–6030, or go to: http://
10101 Hillwood Pkwy., Fort Worth, TX
of cadmium plate or any damage to the www.archives.gov/federal-register/cfr/ibr-
76177; telephone (817) 222–5110; email 9–
piston rod in the Critical Areas as shown in locations.html.
ASW-FTW-AMOC-Requests@faa.gov.
Figure 7 of the Woodward ASB, replace the
(2) For operations conducted under a 14 Issued in Fort Worth, Texas, on April 13,
servo actuator with servo actuator P/N 222–
CFR part 119 operating certificate or under 2016.
382–001–111 or P/N 222–382–001–111FM
14 CFR part 91, subpart K, we suggest that
before further flight. you notify your principal inspector, or Scott A. Horn,
(ii) If there is any corrosion or visible lack lacking a principal inspector, the manager of Acting Manager, Rotorcraft Directorate,
of cadmium plate on the piston rod in areas the local flight standards district office or Aircraft Certification Service.
that are not considered Critical Areas as certificate holding district office, before [FR Doc. 2016–09236 Filed 4–22–16; 8:45 am]
shown in Figure 7 of the Woodward ASB, operating any aircraft complying with this
rework the piston rod by removing any BILLING CODE 4910–13–P
AD through an AMOC.
surface corrosion that has not penetrated into
the base material by lightly buffing. Clean the (i) Additional Information
part using acetone and a nylon bristle brush (1) Bell Alert Service Bulletin (ASB) No. DEPARTMENT OF TRANSPORTATION
to remove any residue. Comply with 222–11–111 for Model 222 and 222B
paragraphs (f)(5) through (f)(6) of this AD. helicopters, ASB No. 222U–11–82 for Model Federal Aviation Administration
Within 1,200 hours time-in-service (TIS) or 1 222U helicopters, ASB No. 230–11–43 for
year, whichever occurs first, replace the Model 230 helicopters, and ASB No. 430–11– 14 CFR Part 39
servo actuator with servo actuator P/N 222– 46 for Model 430 helicopters, all Revision A
382–001–111 or P/N 222–382–001–111FM. and all dated June 22, 2012, which are not [Docket No. FAA–2016–0183; Directorate
(iii) If there is any corrosion that is red or incorporated by reference, contain additional Identifier 2015–SW–016–AD;Amendment
orange in color, magnetic particle inspect the information about the subject of this AD. For 39–18498; AD 2016–08–21]
piston rod for a crack. service information identified in this AD, RIN 2120–AA64
(A) If there is a crack, replace the servo contact Bell Helicopter Textron Canada
actuator with servo actuator, P/N 222–382– Limited, 12,800 Rue de l’Avenir, Mirabel, Airworthiness Directives; Kaman
001–111 or P/N 222–382–001–111FM before Quebec J7J1R4; telephone (450) 437–2862 or Aerospace Corporation
further flight. (800) 363–8023; fax (450) 433–0272; or at
(B) If there is no crack, comply with http://www.bellcustomer.com/files/. You may AGENCY: Federal Aviation
paragraphs (f)(5) through (f)(6) of this AD. review a copy of the service information at Administration (FAA), DOT.
Within 2,400 hours TIS or 2 years, whichever the FAA, Office of the Regional Counsel,
ACTION: Final rule.
jstallworth on DSK7TPTVN1PROD with RULES
occurs first, replace the servo actuator with Southwest Region, 10101 Hillwood Pkwy.,
servo actuator P/N 222–382–001–111 or P/N Room 6N–321, Fort Worth, TX 76177. SUMMARY: We are adopting a new
222–382–001–111FM. (2) The subject of this AD is addressed in
(iv) If there is no corrosion, visible lack of the Transport Canada Civil Aviation (TCCA)
airworthiness directive (AD) for Kaman
cadmium plate, or damage to the piston rod, AD No. CF–2010–29R1, dated July 26, 2012. Aerospace Corporation (Kaman) Model
comply with paragraphs (f)(5) through (f)(6) You may view the TCCA AD on the Internet K–1200 helicopters. This AD requires
of this AD. Within 3,000 hours TIS or 4 years, at http://www.regulations.gov in Docket No. revising the ‘‘Flight Limitations—NO
whichever occurs first, replace the servo FAA–2013–0734. LOAD’’ and ‘‘Flight Limitations—
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![Federal Register / Vol. 81, No. 79 / Monday, April 25, 2016 / Rules and Regulations 24013
LOAD’’ sections of the rotorcraft flight suddenly and causing blade contact We are issuing this rulemaking under
manual (RFM). This AD was prompted with the hub. The report suggests that the authority described in Subtitle VII,
by a report of certain flight maneuvers a rapid aircraft yaw rate and subsequent Part A, Subpart III, Section 44701:
that may lead to main rotor (M/R) blade yaw arresting maneuver may cause low ‘‘General requirements.’’ Under that
to opposing hub contact. These actions clearance of the M/R blades with the section, Congress charges the FAA with
are intended to prevent damage to the opposing M/R hub. This condition promoting safe flight of civil aircraft in
M/R flight controls and subsequent loss could cause an M/R blade to strike the air commerce by prescribing regulations
of control of the helicopter. opposing rotor’s flight controls. The for practices, methods, and procedures
DATES: This AD is effective May 31, proposed requirements were intended to the Administrator finds necessary for
2016. prevent damage to the M/R flight safety in air commerce. This regulation
ADDRESSES: For service information controls and subsequent loss of control is within the scope of that authority
identified in this final rule, contact of the helicopter. because it addresses an unsafe condition
Kaman Aerospace Corporation, Old The NPRM published with the that is likely to exist or develop on
Windsor Rd., P.O. Box 2, Bloomfield, previous mailing address for the Boston products identified in this rulemaking
Connecticut 06002–0002; telephone Aircraft Certification Office. We have action.
(860) 242–4461; fax (860) 243–7047; or revised this contact information in this Regulatory Findings
at http://www.kamanaero.com. You may final rule to reflect the new mailing
address. This AD will not have federalism
review a copy of the referenced service
implications under Executive Order
information at the FAA, Office of the Comments 13132. This AD will not have a
Regional Counsel, Southwest Region,
We gave the public the opportunity to substantial direct effect on the States, on
10101 Hillwood Pkwy., Room 6N–321,
participate in developing this AD, but the relationship between the national
Fort Worth, TX 76177.
we did not receive any comments on the government and the States, or on the
Examining the AD Docket NPRM (81 FR 3344, January 21, 2016). distribution of power and
You may examine the AD docket on responsibilities among the various
FAA’s Determination levels of government.
the Internet at http://
www.regulations.gov by searching for We have reviewed the relevant For the reasons discussed above, I
and locating Docket No. FAA–2016– information and determined that an certify that this AD:
0183; or in person at the Docket unsafe condition exists and is likely to (1) Is not a ‘‘significant regulatory
Operations Office between 9 a.m. and 5 exist or develop on other products of the action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
p.m., Monday through Friday, except same type design and that air safety and
DOT Regulatory Policies and Procedures
Federal holidays. The AD docket the public interest require adopting the
(44 FR 11034, February 26, 1979);
contains this AD, the economic AD requirements as proposed. (3) Will not affect intrastate aviation
evaluation, any comments received, and in Alaska to the extent that it justifies
Related Service Information
other information. The street address for making a regulatory distinction; and
the Docket Operations Office (phone: Kaman has issued Kaman K–1200 (4) Will not have a significant
800–647–5527) is U.S. Department of RFM, Revision 5, dated April 14, 2015. economic impact, positive or negative,
Transportation, Docket Operations This revision of the limitations section on a substantial number of small entities
Office, M–30, West Building Ground of the RFM inserts, for both load under the criteria of the Regulatory
Floor, Room W12–140, 1200 New Jersey operations and no load operations, a Flexibility Act.
Avenue SE., Washington, DC 20590. warning and limitations about departing We prepared an economic evaluation
FOR FURTHER INFORMATION CONTACT: Kirk from rearward to forward flight, a of the estimated costs to comply with
Gustafson, Aviation Safety Engineer, maximum rearward flight speed of 25 this AD and placed it in the AD docket.
Boston Aircraft Certification Office, knots, a maximum sideward flight speed
Engine & Propeller Directorate, FAA, of 17 knots, and a prohibition on List of Subjects in 14 CFR Part 39
1200 District Avenue, Burlington, weather-vanning takeoffs and Air transportation, Aircraft, Aviation
Massachusetts 01803; telephone (781) departures as a method to turn aircraft. safety, Incorporation by reference,
238–7190; email kirk.gustafson@faa.gov. Costs of Compliance Safety.
SUPPLEMENTARY INFORMATION:
We estimate that this AD will affect Adoption of the Amendment
Discussion 16 helicopters of U.S. Registry. We Accordingly, under the authority
On January 21, 2016, at 81 FR 3344, estimate that operators may incur the delegated to me by the Administrator,
the Federal Register published our following costs in order to comply with the FAA amends 14 CFR part 39 as
notice of proposed rulemaking (NPRM), this AD. At an average labor rate of $85 follows:
which proposed to amend 14 CFR part per work-hour, we expect revising the
39 by adding an AD that would apply RFM will require 0.5 work-hour, for cost PART 39—AIRWORTHINESS
to Kaman Model K–1200 helicopters. of about $43 per helicopter, or $688 for DIRECTIVES
The NPRM proposed to require revising the U.S. fleet.
the ‘‘Flight Limitations–NO LOAD’’ and ■ 1. The authority citation for part 39
Authority for This Rulemaking continues to read as follows:
‘‘Flight Limitations–LOAD’’ sections of
the RFM by inserting a warning and Title 49 of the United States Code Authority: 49 U.S.C. 106(g), 40113, 44701.
jstallworth on DSK7TPTVN1PROD with RULES
limitations about rearward to forward specifies the FAA’s authority to issue
§ 39.13 [Amended]
flight, establishing maximum rearward rules on aviation safety. Subtitle I,
and sideward flight speeds, and section 106, describes the authority of ■ 2. The FAA amends § 39.13 by adding
prohibiting weather-vanning takeoffs the FAA Administrator. Subtitle VII: the following new airworthiness
and departures to turn the helicopter. Aviation Programs, describes in more directive (AD):
The NPRM was prompted by a report of detail the scope of the Agency’s 2016–08–21 Kaman Aerospace Corporation
a Model K–1200 helicopter turning authority. (Kaman): Amendment 39–18498; Docket
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Document Created: 2016-04-23 01:39:19
Document Modified: 2016-04-23 01:39:19
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective May 31, 2016. | |
| Contact | Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7190; email [email protected] | |
| FR Citation | 81 FR 24012 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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