82 FR 24030 - Airworthiness Directives; Piper Aircraft, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 100 (May 25, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 100 (May 25, 2017)
| Page Range | 24030-24033 | |
| FR Document | 2017-10407 |
[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)] [Rules and Regulations] [Pages 24030-24033] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10407] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9550; Directorate Identifier 2016-CE-026-AD; Amendment 39-18894; AD 2017-10-20] RIN 2120-AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes. This AD was prompted by fatigue cracking in the fuselage station (FS) 332.00 bulkhead common to the horizontal stabilizer front spar attachment. This AD requires repetitive inspections to detect cracks in the bulkhead and any necessary repairs. This AD also provides an optional modification if no cracks are found that will greatly reduce the likelihood of the specified cracks. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective June 29, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 29, 2017. ADDRESSES: For service information identified in this final rule, contact Piper Aircraft, Inc., Customer Service, 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (877) 879-0275; fax: none; email: [email protected]; Internet: www.piper.com. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9550. 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- 9550; 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 AD, the regulatory [[Page 24031]] evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647-5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Gregory ``Keith'' Noles, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474-5551; fax: (404) 474-5606; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes. The NPRM published in the Federal Register on January 3, 2017 (82 FR 48). The NPRM was prompted by reports of fatigue cracking in the FS 332.00 bulkhead common to the horizontal stabilizer front spar attachment on Piper Aircraft, Inc. PA-31 airplanes. Cracks in the bulkhead could compromise the structural component's capability to carry flight loads, increasing the potential to overload and fail adjacent structure. The NPRM proposed to provide an optional modification if no cracks are found that will greatly reduce the likelihood of the specified cracks. We are issuing this AD to detect and repair cracks in the bulkhead that could lead to structural failure and result in loss of control. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request Change to Labor Estimates Joe M. Miller, Chief Inspector for Warbelow's Air Ventures, Inc. in Fairbanks, Alaska, stated they have complied with the proposed requirement on 3 airplanes and find that it takes 2 mechanics about 6 hours each (12 man-hours) to accomplish just the inspection phase. The commenter states that to better access the affected areas it is easier to remove both horizontal stabilizers. In total, it takes a crew of 2 about 4 days (64 man-hours) to accomplish the complete process from inspection to return to service. We partially agree. We agree with revising the labor estimates for both the inspection and modification because of the additional operator data. Also, we will ensure the access time is included in both the inspection and modification estimates. Because the original time estimate was provided by another experienced operator, we will update the estimate to reflect an average of the two reported times. We disagree with using a combined estimate of 64 hours because the inspection and modification are estimated separately. We will make the following changes to the AD based on this comment:Update the inspection labor estimate from 1 hour to 12 hours; and Update the modification labor estimate from 26 to 45 hours. Question on Airplanes That Have Previously Complied Joe M. Miller, Chief Inspector, Warbelow's Air Ventures, Inc., Fairbanks, Alaska, asked that we provide reference to those airplanes that have previously complied with Service Bulletin 1289A and installed kit 88578-001 Rev B. The commenter stated the NPRM only addresses the initial inspection and modification of FS 332 and does not address airplanes that have previously complied with Piper MSB 1289A by inspection and subsequent installation of the Piper Kit 88578-001 Rev B. We do not agree because paragraph (f) of the AD addresses this situation with the phrase ``unless already done.'' We have not changed the AD based on this comment. Request To Extend the Initial Compliance Time Roger Braun asked that we extend the initial compliance time because his impression is that the cracks were found solely on one very high-time (20,000 hour plus) airplane, and he perceives 3,000 hours time-in-service (TIS) as too early to start the inspection intervals based on the finding. We do not agree because the airplane design is intended to provide a service life that is crack-free. When cracks are found in service, a management program is put in place (reference Advisory Circular 91-82). It is true that the crack was found on an airplane with over 20,000 hours. The compliance time for the management program is based on the known failure time but must include safety and statistical reduction factors (reference Advisory Circular 23-13). Starting inspections at 3,000 hours TIS ensures any cracks that form will be found early enough to prevent an unsafe condition. While it may appear excessive, the compliance time is set to meet the design intent of a crack-free operation. We have not changed the AD based on this comment. Request for a Visual Inspection Roger Braun asked that we allow for a visual inspection instead of a penetrant inspection because the parts involve a simple visual inspection. The commenter suggested that 10x glass would suffice instead of stripping paint and doing a dye-penetrant inspection. Then, a penetrant could be used if any cracks are suspected. We do not agree because the cleaning and penetrant method has higher detection reliability than a purely visual method. The reliability of the inspection method is tied to the compliance time for the repetitive inspection and deferral of the permanent modification. Once the AD is published, the commenter may request an alternative method of compliance (AMOC) for the visual inspection method. The request, including all substantiating data, may be submitted following 14 CFR 39.19 as specified in paragraph (i)(1) of this AD. We have not changed the AD based on this comment. Clarification on Installation of the Kit Tim Glubaskas, Director of Maintenance, Warbelow's Air Ventures, asked for a clarification on whether installation of the kit terminates the repetitive inspections. That kit installation is terminating action for the repetitive inspection. This is addressed in paragraph (g)(3)(i) of this AD when the kit is used as a repair for cracks and in paragraph (g)(4) of this AD when the kit is used as a modification with no cracks. We have not changed the AD based on this comment. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes: Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. [[Page 24032]] Related Service Information Under 1 CFR Part 51 We reviewed Piper Aircraft, Inc. Service Bulletin No. 1289A, dated October 26, 2016. The service information describes procedures for the repetitive inspections, necessary repairs, and the optional modification of the bulkhead. 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. Costs of Compliance We estimate that this AD affects 955 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspect for cracks in the 12 work-hours x $85 Not Applicable........... $1,020 $974,100 bulkhead. per hour = $1,020. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs/ replacements that would be required based on the results of the inspection. We have no way of determining the number of airplanes that might need these repairs/replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product --------------------------------------------------------------------------------------------------------------- Repair/Modification.......................... 45 work-hours x $85 per hour = $296 $4,121 $3,825. ---------------------------------------------------------------------------------------------------------------- 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, 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. 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): 2017-10-20 Piper Aircraft, Inc.: Amendment 39-18894; Docket No. FAA- 2016-9550; Directorate Identifier 2016-CE-026-AD. (a) Effective Date This AD is effective June 29, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Piper Aircraft, Inc. Navajo Models PA-31, PA- 31-300, and PA-31-325, serial numbers 31-2 through 31-900, and 31- 7300901 through 31-8312019; and Chieftain/T-1020 Models PA-31-350, serial numbers 31-5001 through 31-5004, and 31-7305005 through 31- 8553002, certificated in any category. Note 1 to paragraph (c) of this AD: The Model PA-31 may also be identified as a PA-31-310 even though the PA-31-310 is not a model recognized by the Federal Aviation Administration (FAA) on the type certificate data sheet. (d) Subject Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 5312: Fuselage--Main Bulkhead. (e) Unsafe Condition This AD was prompted by fatigue cracking in the fuselage station (FS) 332.00 bulkhead common to the horizontal stabilizer front spar attachment. This AD requires repetitive inspections to detect cracks in the bulkhead and any necessary repairs. This AD also provides an optional modification if no cracks are found that will greatly reduce the likelihood of the specified cracks. Cracks in the bulkhead could compromise the structural components capability to carry flight loads, increasing the potential to overload and fail adjacent structure and lead to loss of control. (f) Compliance Comply with paragraphs (g)(1) through (3) of this AD within the compliance times specified, unless already done. [[Page 24033]] (g) Actions (1) For airplanes with 3,000 hours time-in-service (TIS) or less as of June 29, 2017 (the effective date of this AD): Initially within 500 hours TIS after reaching 3,000 hours TIS and repetitively thereafter every 200 hours TIS, inspect the fuselage station (FS) 332.00 bulkhead assembly for cracks following the instructions in Part I of Piper Aircraft, Inc. Service Bulletin (SB) No. 1289A, dated October 26, 2016. (2) For airplanes with over 3,000 hours TIS as of June 29, 2017 (the effective date of this AD): Initially within the next 500 hours TIS after June 29, 2017 (the effective date of this AD) and repetitively thereafter every 200 hours TIS, inspect the FS 332.00 bulkhead assembly for cracks, following the instructions in Part I of Piper Aircraft, Inc. SB No. 1289A, dated October 26, 2016. (3) If cracks are found during any of the inspections required in paragraphs (g)(1) or (2) of this AD, before further flight, repair the cracks following the modification instructions in Part II of Piper Aircraft, Inc. SB No. 1289A, dated October 26, 2016, and one of the following as applicable: (i) If the crack does not extend beyond the inspection/template area of figure 2 of Piper Aircraft, Inc. SB No. 1289A, dated October 26, 2016, and meets the minimum acceptable distance in figure 3 and table 2 of Part II of Piper Aircraft, Inc. SB No. 1289A, dated October 26, 2016, then the installation of Piper Kit 88578-001 Revision B, dated June 23, 2016, is acceptable as a repair and is considered terminating action for the repetitive inspection requirement in paragraphs (g)(1) and (2) of this AD. (ii) If the crack extends beyond the inspection/template area of figure 2 of Piper Aircraft, Inc. SB No. 1289A, dated October 26, 2016, or does not meet the minimum acceptable distance in figure 3 and table 2 of Part II of Piper Aircraft, Inc. SB No. 1289A, dated October 26, 2016, then the installation of Piper Kit 88578-001 Revision B, dated June 23, 2016, is not an acceptable repair. You must obtain an alternative method of compliance (AMOC) for any repair or modification in this area. You may contact Piper Aircraft, Inc. for repair instruction development specific to this condition. For contact information refer to paragraph (j) of this AD. (4) If no cracks are found, you may install Piper Kit 88578-001 Revision B, dated June 23, 2016, on an uncracked bulkhead following the Modification instructions in Part II of Piper Aircraft, Inc. SB No. 1289A, dated October 26, 2016. Installation of Piper Kit 88578- 001 Revision B, dated June 23, 2016, on an uncracked bulkhead is considered terminating action for the repetitive inspection requirement in paragraphs (g)(1) and (2) of this AD. (h) Special Flight Permit A special flight permit is allowed for this AD per 14 CFR 39.23 with limitations. Permits are only allowed for the inspections required by this AD and are not allowed if cracks are discovered during any inspection following Part I of Piper Aircraft, Inc. SB No. 1289A, dated October 26, 2016. Any cracks found during any inspection must be repaired before further flight. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (k) of this AD. (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. (j) Related Information (1) For more information about this AD, contact Gregory ``Keith'' Noles, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474-5551; fax: (404) 474-5606; email: [email protected]. (2) For service information identified in this AD, contact Piper Aircraft, Inc., Customer Service, 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (877) 879-0275; fax: none; email: [email protected]; Internet: www.piper.com. You may review the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. (k) Related Information For more information about this AD, contact Gregory ``Keith'' Noles, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474-5551; fax: (404) 474-5606; email: [email protected]. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Piper Aircraft, Inc. Service Bulletin No. 1289A, dated October 26, 2016. (ii) Reserved. (3) For Piper Aircraft, Inc. service information identified in this AD, contact Piper Aircraft, Inc., Customer Service, 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (877) 879-0275; fax: none; email: [email protected]; Internet: www.piper.com. (4) You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816-329-4148. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on May 10, 2017. Melvin Johnson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-10407 Filed 5-24-17; 8:45 am] BILLING CODE 4910-13-P
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(k) Terminating Action for Certain Ave. SW., Washington, DC 20591, Attn: DEPARTMENT OF TRANSPORTATION
Requirements of Other ADs Information Collection Clearance Officer,
(1) Accomplishing the actions required by AES–200. Federal Aviation Administration
paragraph (g) of this AD terminates the
(n) Related Information
actions required by paragraphs (a) and (b) of 14 CFR Part 39
AD 98–25–07. (1) Refer to Mandatory Continuing
(2) Accomplishing the actions required by Airworthiness Information (MCAI) EASA [Docket No. FAA–2016–9550; Directorate
paragraph (g) of this AD terminates the Airworthiness Directive 2015–0232R1, dated Identifier 2016–CE–026–AD; Amendment
actions required by paragraphs (i) and (j) of 39–18894; AD 2017–10–20]
December 16, 2015, for related information.
AD 2012–25–06. This MCAI may be found in the AD docket RIN 2120–AA64
(l) Reporting Requirements on the Internet at http://www.regulations.gov
Within 60 days after any inspection by searching for and locating Docket No. Airworthiness Directives; Piper
required by paragraph (g) of this AD, or FAA–2015–0084. Aircraft, Inc. Airplanes
within 60 days after the effective date of this (2) Service information identified in this
AGENCY: Federal Aviation
AD, whichever occurs later, report any AD that is not incorporated by reference is
findings, positive or negative, to Airbus available at the addresses specified in
Administration (FAA), DOT.
Service Bulletin Reporting Online paragraphs (o)(3) and (o)(4) of this AD. ACTION: Final rule.
Application on Airbus World (https://
w3.airbus.com/). (o) Material Incorporated by Reference SUMMARY: We are adopting a new
(1) The Director of the Federal Register airworthiness directive (AD) for certain
(m) Other FAA AD Provisions
approved the incorporation by reference Piper Aircraft, Inc. Models PA–31, PA–
The following provisions also apply to this 31–300, PA–31–325, and PA–31–350
AD: (IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR airplanes. This AD was prompted by
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International part 51. fatigue cracking in the fuselage station
Branch, ANM–116, Transport Airplane (2) You must use this service information (FS) 332.00 bulkhead common to the
Directorate, FAA, has the authority to as applicable to do the actions required by horizontal stabilizer front spar
approve AMOCs for this AD, if requested this AD, unless this AD specifies otherwise. attachment. This AD requires repetitive
using the procedures found in 14 CFR 39.19. (i) Airbus Service Bulletin A300–57–0261, inspections to detect cracks in the
In accordance with 14 CFR 39.19, send your dated June 11, 2015. bulkhead and any necessary repairs.
request to your principal inspector or local (ii) Airbus Service Bulletin A300–57–6117, This AD also provides an optional
Flight Standards District Office, as
dated May 28, 2015. modification if no cracks are found that
appropriate. If sending information directly
to the International Branch, send it to ATTN: (3) For service information identified in will greatly reduce the likelihood of the
Dan Rodina, Aerospace Engineer, this AD, contact Airbus SAS, Airworthiness specified cracks. We are issuing this AD
International Branch, ANM–116, Transport Office—EAW, 1 Rond Point Maurice to correct the unsafe condition on these
Airplane Directorate, FAA, 1601 Lind Bellonte, 31707 Blagnac Cedex, France; products.
Avenue SW., Renton, WA 98057–3356; telephone +33 5 61 93 36 96; fax +33 5 61 DATES: This AD is effective June 29,
telephone 425–227–2125; fax 425–227–1149. 93 44 51; email account.airworth-eas@ 2017.
Information may be emailed to: 9-ANM-116- airbus.com; Internet http://www.airbus.com. The Director of the Federal Register
AMOC-REQUESTS@faa.gov. Before using (4) You may view this service information
any approved AMOC, notify your appropriate approved the incorporation by reference
at the FAA, Transport Airplane Directorate, of a certain publication listed in this AD
principal inspector, or lacking a principal 1601 Lind Avenue SW., Renton, WA. For
inspector, the manager of the local flight as of June 29, 2017.
information on the availability of this
standards district office/certificate holding ADDRESSES: For service information
district office. material at the FAA, call 425–227–1221.
(5) You may view this service information identified in this final rule, contact
(2) Contacting the Manufacturer: For any Piper Aircraft, Inc., Customer Service,
requirement in this AD to obtain corrective that is incorporated by reference at the
National Archives and Records 2926 Piper Drive, Vero Beach, Florida
actions from a manufacturer, the action must
be accomplished using a method approved Administration (NARA). For information on 32960; telephone: (877) 879–0275; fax:
by the Manager, International Branch, ANM– the availability of this material at NARA, call none; email: customer.service@
116, Transport Airplane Directorate, FAA; or 202–741–6030, or go to: http:// piper.com; Internet: www.piper.com.
EASA; or Airbus’s EASA DOA. If approved www.archives.gov/federal-register/cfr/ibr- You may view this referenced service
by the DOA, the approval must include the locations.html. information at the FAA, Small Airplane
DOA-authorized signature. Directorate, 901 Locust, Kansas City,
(3) Reporting Requirements: A federal Issued in Renton, Washington, on May 2, Missouri 64106. For information on the
agency may not conduct or sponsor, and a 2017.
availability of this material at the FAA,
person is not required to respond to, nor Michael Kaszycki, call (816) 329–4148. It is also available
shall a person be subject to a penalty for
failure to comply with a collection of
Acting Manager, Transport Airplane on the internet at http://
information subject to the requirements of Directorate, Aircraft Certification Service. www.regulations.gov by searching for
the Paperwork Reduction Act unless that [FR Doc. 2017–10285 Filed 5–24–17; 8:45 am] and locating Docket No. FAA–2016–
collection of information displays a current BILLING CODE 4910–13–P 9550.
valid OMB Control Number. The OMB
Control Number for this information Examining the AD Docket
collection is 2120–0056. Public reporting for You may examine the AD docket on
this collection of information is estimated to the Internet at http://
be approximately 5 minutes per response, www.regulations.gov by searching for
including the time for reviewing instructions,
and locating Docket No. FAA–2016–
completing and reviewing the collection of
information. All responses to this collection 9550; or in person at the Docket
of information are mandatory. Comments Management Facility between 9 a.m.
concerning the accuracy of this burden and and 5 p.m., Monday through Friday,
suggestions for reducing the burden should except Federal holidays. The AD docket
be directed to the FAA at: 800 Independence contains this AD, the regulatory
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Related Service Information Under 1 and the optional modification of the Costs of Compliance
CFR Part 51 bulkhead. This service information is
reasonably available because the We estimate that this AD affects 955
We reviewed Piper Aircraft, Inc. airplanes of U.S. registry.
Service Bulletin No. 1289A, dated interested parties have access to it
October 26, 2016. The service through their normal course of business We estimate the following costs to
information describes procedures for the or by the means identified in the comply with this AD:
repetitive inspections, necessary repairs, ADDRESSES section.
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspect for cracks in the bulkhead ............... 12 work-hours × $85 per hour = $1,020 ..... Not Applicable .... $1,020 $974,100
We estimate the following costs to do of the inspection. We have no way of that might need these repairs/
any necessary repairs/replacements that determining the number of airplanes replacements:
would be required based on the results
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair/Modification ...................................................... 45 work-hours × $85 per hour = $3,825 .................... $296 $4,121
Authority for This Rulemaking (2) Is not a ‘‘significant rule’’ under (b) Affected ADs
DOT Regulatory Policies and Procedures None.
Title 49 of the United States Code (44 FR 11034, February 26, 1979),
specifies the FAA’s authority to issue (c) Applicability
(3) Will not affect intrastate aviation
rules on aviation safety. Subtitle I, This AD applies to Piper Aircraft, Inc.
in Alaska, and
section 106, describes the authority of Navajo Models PA–31, PA–31–300, and PA–
the FAA Administrator. Subtitle VII: (4) Will not have a significant 31–325, serial numbers 31–2 through 31–900,
Aviation Programs, describes in more economic impact, positive or negative, and 31–7300901 through 31–8312019; and
detail the scope of the Agency’s on a substantial number of small entities Chieftain/T–1020 Models PA–31–350, serial
authority. under the criteria of the Regulatory numbers 31–5001 through 31–5004, and 31–
Flexibility Act. 7305005 through 31–8553002, certificated in
We are issuing this rulemaking under any category.
the authority described in Subtitle VII, List of Subjects in 14 CFR Part 39 Note 1 to paragraph (c) of this AD: The
Part A, Subpart III, Section 44701: Model PA–31 may also be identified as a PA–
‘‘General requirements.’’ Under that Air transportation, Aircraft, Aviation
31–310 even though the PA–31–310 is not a
section, Congress charges the FAA with safety, Incorporation by reference,
model recognized by the Federal Aviation
promoting safe flight of civil aircraft in Safety. Administration (FAA) on the type certificate
air commerce by prescribing regulations Adoption of the Amendment data sheet.
for practices, methods, and procedures
Accordingly, under the authority (d) Subject
the Administrator finds necessary for
safety in air commerce. This regulation delegated to me by the Administrator, Joint Aircraft System Component (JASC)/
is within the scope of that authority the FAA amends 14 CFR part 39 as Air Transport Association (ATA) of America
follows: Code 5312: Fuselage—Main Bulkhead.
because it addresses an unsafe condition
that is likely to exist or develop on (e) Unsafe Condition
products identified in this rulemaking PART 39—AIRWORTHINESS
This AD was prompted by fatigue cracking
action. DIRECTIVES
in the fuselage station (FS) 332.00 bulkhead
common to the horizontal stabilizer front
Regulatory Findings ■ 1. The authority citation for part 39 spar attachment. This AD requires repetitive
continues to read as follows: inspections to detect cracks in the bulkhead
This AD will not have federalism
implications under Executive Order Authority: 49 U.S.C. 106(g), 40113, 44701. and any necessary repairs. This AD also
provides an optional modification if no
13132. This AD will not have a § 39.13 [Amended] cracks are found that will greatly reduce the
substantial direct effect on the States, on likelihood of the specified cracks. Cracks in
the relationship between the national ■ 2. The FAA amends § 39.13 by adding the bulkhead could compromise the
government and the States, or on the the following new airworthiness structural components capability to carry
distribution of power and directive (AD): flight loads, increasing the potential to
responsibilities among the various 2017–10–20 Piper Aircraft, Inc.: overload and fail adjacent structure and lead
levels of government. Amendment 39–18894; Docket No. to loss of control.
For the reasons discussed above, I FAA–2016–9550; Directorate Identifier
(f) Compliance
certify that this AD: 2016–CE–026–AD.
Comply with paragraphs (g)(1) through (3)
(1) Is not a ‘‘significant regulatory (a) Effective Date of this AD within the compliance times
action’’ under Executive Order 12866, This AD is effective June 29, 2017. specified, unless already done.
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(g) Actions (i) Alternative Methods of Compliance National Archives and Records
(1) For airplanes with 3,000 hours time-in- (AMOCs) Administration (NARA). For information on
service (TIS) or less as of June 29, 2017 (the (1) The Manager, Atlanta Aircraft the availability of this material at NARA, call
effective date of this AD): Initially within 500 Certification Office, FAA, has the authority to 202–741–6030, or go to: http://
hours TIS after reaching 3,000 hours TIS and approve AMOCs for this AD, if requested www.archives.gov/federal-register/cfr/ibr-
repetitively thereafter every 200 hours TIS, using the procedures found in 14 CFR 39.19. locations.html.
inspect the fuselage station (FS) 332.00 In accordance with 14 CFR 39.19, send your Issued in Kansas City, Missouri, on May
bulkhead assembly for cracks following the request to your principal inspector or local 10, 2017.
instructions in Part I of Piper Aircraft, Inc. Flight Standards District Office, as Melvin Johnson,
Service Bulletin (SB) No. 1289A, dated appropriate. If sending information directly
October 26, 2016. to the manager of the ACO, send it to the Acting Manager, Small Airplane Directorate,
(2) For airplanes with over 3,000 hours TIS attention of the person identified in Aircraft Certification Service.
as of June 29, 2017 (the effective date of this paragraph (k) of this AD. [FR Doc. 2017–10407 Filed 5–24–17; 8:45 am]
AD): Initially within the next 500 hours TIS (2) Before using any approved AMOC, BILLING CODE 4910–13–P
after June 29, 2017 (the effective date of this notify your appropriate principal inspector,
AD) and repetitively thereafter every 200 or lacking a principal inspector, the manager
hours TIS, inspect the FS 332.00 bulkhead of the local flight standards district office/
assembly for cracks, following the
DEPARTMENT OF TRANSPORTATION
certificate holding district office.
instructions in Part I of Piper Aircraft, Inc. SB
No. 1289A, dated October 26, 2016. (j) Related Information Federal Aviation Administration
(3) If cracks are found during any of the (1) For more information about this AD,
inspections required in paragraphs (g)(1) or contact Gregory ‘‘Keith’’ Noles, Aerospace 14 CFR Part 39
(2) of this AD, before further flight, repair the Engineer, FAA, Atlanta Aircraft Certification
cracks following the modification [Docket No. FAA–2017–0114; Directorate
Office, 1701 Columbia Avenue, College Park,
instructions in Part II of Piper Aircraft, Inc. Identifier 2017–NE–03–AD; Amendment 39–
Georgia 30337; phone: (404) 474–5551; fax:
SB No. 1289A, dated October 26, 2016, and 18880; AD 2017–10–06]
(404) 474–5606; email: gregory.noles@
one of the following as applicable: faa.gov. RIN 2120–AA64
(i) If the crack does not extend beyond the (2) For service information identified in
inspection/template area of figure 2 of Piper this AD, contact Piper Aircraft, Inc., Airworthiness Directives; Rolls-Royce
Aircraft, Inc. SB No. 1289A, dated October Customer Service, 2926 Piper Drive, Vero
26, 2016, and meets the minimum acceptable plc Turbofan Engines
Beach, Florida 32960; telephone: (877) 879–
distance in figure 3 and table 2 of Part II of 0275; fax: none; email: customer.service@ AGENCY: Federal Aviation
Piper Aircraft, Inc. SB No. 1289A, dated piper.com; Internet: www.piper.com. You
October 26, 2016, then the installation of Administration (FAA), DOT.
may review the referenced service
Piper Kit 88578–001 Revision B, dated June ACTION: Final rule; request for
information at the FAA, Small Airplane
23, 2016, is acceptable as a repair and is Directorate, 901 Locust, Kansas City, comments.
considered terminating action for the
Missouri 64106. For information on the
repetitive inspection requirement in
availability of this material at the FAA, call SUMMARY: We are adopting a new
paragraphs (g)(1) and (2) of this AD. airworthiness directive (AD) for certain
(816) 329–4148.
(ii) If the crack extends beyond the Rolls-Royce plc (RR) RB211 Trent 768–
inspection/template area of figure 2 of Piper (k) Related Information 60, 772–60, and 772B–60 turbofan
Aircraft, Inc. SB No. 1289A, dated October
For more information about this AD, engines. This AD requires fluorescent
26, 2016, or does not meet the minimum
contact Gregory ‘‘Keith’’ Noles, Aerospace penetrant inspection (FPI) of the
acceptable distance in figure 3 and table 2 of
Engineer, FAA, Atlanta Aircraft Certification compressor intermediate case (CIC) for
Part II of Piper Aircraft, Inc. SB No. 1289A,
Office, 1701 Columbia Avenue, College Park,
dated October 26, 2016, then the installation cracking. This AD was prompted by
of Piper Kit 88578–001 Revision B, dated Georgia 30337; phone: (404) 474–5551; fax:
(404) 474–5606; email: gregory.noles@ CICs that were weld repaired and have
June 23, 2016, is not an acceptable repair. a higher probability of cracking as a
You must obtain an alternative method of faa.gov.
result of the weld repair process. We are
compliance (AMOC) for any repair or (l) Material Incorporated by Reference
modification in this area. You may contact
issuing this AD to correct the unsafe
Piper Aircraft, Inc. for repair instruction (1) The Director of the Federal Register condition on these products.
approved the incorporation by reference
development specific to this condition. For DATES: This AD becomes effective June
contact information refer to paragraph (j) of (IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR 9, 2017.
this AD. The Director of the Federal Register
(4) If no cracks are found, you may install part 51.
(2) You must use this service information approved the incorporation by reference
Piper Kit 88578–001 Revision B, dated June
23, 2016, on an uncracked bulkhead as applicable to do the actions required by of a certain publication listed in this AD
following the Modification instructions in this AD, unless the AD specifies otherwise. as of June 9, 2017.
Part II of Piper Aircraft, Inc. SB No. 1289A, (i) Piper Aircraft, Inc. Service Bulletin No. We must receive comments on this
dated October 26, 2016. Installation of Piper 1289A, dated October 26, 2016. AD by July 10, 2017.
Kit 88578–001 Revision B, dated June 23, (ii) Reserved.
ADDRESSES: You may send comments by
2016, on an uncracked bulkhead is (3) For Piper Aircraft, Inc. service
information identified in this AD, contact any of the following methods:
considered terminating action for the
repetitive inspection requirement in Piper Aircraft, Inc., Customer Service, 2926 • Federal eRulemaking Portal: Go to
paragraphs (g)(1) and (2) of this AD. Piper Drive, Vero Beach, Florida 32960; http://www.regulations.gov. Follow the
telephone: (877) 879–0275; fax: none; email: instructions for submitting comments.
(h) Special Flight Permit customer.service@piper.com; Internet: • Mail: U.S. Department of
A special flight permit is allowed for this www.piper.com. Transportation, 1200 New Jersey
AD per 14 CFR 39.23 with limitations. (4) You may view this referenced service Avenue SE., West Building Ground
Permits are only allowed for the inspections information at the FAA, Small Airplane
Floor, Room W12–140, Washington, DC
required by this AD and are not allowed if Directorate, 901 Locust, Kansas City,
cracks are discovered during any inspection Missouri 64106. For information on the 20590–0001.
following Part I of Piper Aircraft, Inc. SB No. availability of this material at the FAA, call • Hand Delivery: Deliver to Mail
1289A, dated October 26, 2016. Any cracks 816–329–4148. address above between 9 a.m. and 5
found during any inspection must be (5) You may view this service information p.m., Monday through Friday, except
repaired before further flight. that is incorporated by reference at the Federal holidays.
VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 E:\FR\FM\25MYR1.SGM 25MYR1](https://thefederalregister.org/doc/82_FR_24130/page/4.svg)
Document Created: 2018-11-08 08:53:26
Document Modified: 2018-11-08 08:53:26
| 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 June 29, 2017. | |
| Contact | Gregory ``Keith'' Noles, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474-5551; fax: (404) 474-5606; email: [email protected] | |
| FR Citation | 82 FR 24030 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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