Document ID: FAA-2020-1006-0002
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Piper Aircraft, Inc. Airplanes
Posted Date: 2021-12-21T05:00Z

[Federal Register Volume 86, Number 242 (Tuesday, December 21, 2021)]
[Rules and Regulations]
[Pages 72186-72188]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-27510]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1006; Project Identifier 2019-CE-047-AD; Amendment 
39-21855; AD 2021-25-11]
RIN 2120-AA64

Airworthiness Directives; Piper Aircraft, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 78-02-03, 
which applied to all Piper Aircraft, Inc. (Piper) Model PA-23-250 
airplanes. AD 78-02-03 required repetitively inspecting the stabilator 
tip tube and weight assemblies for cracks, inspecting for missing 
rivets and screws, replacing the forward rib/horn assemblies, and 
reinforcing the mounting. Since AD 78-02-03 was issued, Piper developed 
a newly-designed stabilator, which is not subject to the unsafe 
condition, and revised its service information. This AD retains the 
actions of AD 78-02-03, but reduces the applicability and requires the 
actions in the revised service information. The FAA is issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective January 25, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 25, 
2022.

ADDRESSES: For service information identified in this final rule, 
contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, FL 32960; 
phone: (772) 299-2141; website: https://www.piper.com/. You may view 
this service information at the FAA, Airworthiness Products Section, 
Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For 
information on the availability of this material at the FAA, call (817) 
222-5110. It is also available at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-1006.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-1006; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this final rule, any 
comments received, and other information. The street address for Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: John Marshall, Aviation Safety 
Engineer, Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park, 
GA 30337; phone: (404) 474-5524; fax: (404) 474-5605; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by superseding AD 78-02-03 [Reg. Docket No. 77-EA-81, 
Amendment 39-3128] (43 FR 3079, January 23, 1978) (AD 78-02-03). AD 78-
02-03 applied to all Piper Model PA-23-250 airplanes and required 
repetitively inspecting both the stabilator tip tube and weight 
assemblies for cracks. For different groups of serial-numbered 
airplanes, AD 78-02-03 required a one-time inspection of the stabilator 
tip ribs for missing rivets and screws, replacement of the forward rib/
horn assemblies, and reinforcement of the mounting. The repetitive 
inspections in AD 78-02-03 for all serial-numbered airplanes had no 
terminating action and were required regardless of any corrective 
actions performed.
    The NPRM published in the Federal Register on September 16, 2021 
(86 FR 51636). The NPRM was prompted by Piper developing a newly-
designed stabilator, which is not subject to the unsafe condition, and 
revising its service information. The FAA determined the applicability 
of AD 78-02-03 should be revised to exclude airplanes beginning with 
serial number 27-7954122, which were manufactured with the stabilator 
design change. In the NPRM, the FAA proposed to retain all of the 
requirements of AD 78-02-03 but reduce the applicability and update 
some of the service information that would be required for compliance. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
requires adopting this AD as proposed. Accordingly, the FAA is issuing 
this AD to address the unsafe condition on these products. This AD is 
adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed the following service documents required for 
compliance with this AD:
     Piper Service Bulletin (SB) No. 547, dated March 1, 1977, 
which contains instructions for inspecting the stabilator tip rib;
     Piper SB No. 569, dated August 24, 1977, which contains 
information for replacing the stabilator tab horn;
     Piper Service Letter No. 807A, dated September 8, 1977, 
which contains information for installing the stabilator outboard nose 
rib; and
     Piper SB No. 540B, February 9, 2021, which contains 
instructions for inspecting the stabilator tip tube and weight assembly 
and addressing any cracks found.
    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.

Other Related Service Information

    The FAA reviewed the following documents for information related to 
this AD:
     Piper SB 540, which contains instructions for inspecting 
and reinforcing the stabilator tip tube and weight assembly; and
     Piper Aztec Service Manual, Part Number 753-564, dated 
January 1, 2009. Paragraphs 4-65 through 4-67 of this manual contain 
procedures for checking control surface balance.

[[Page 72187]]

Differences Between This AD and the Service Information

    Piper SB 540B specifies contacting Piper for repair instructions. 
This AD requires contacting the FAA for an approved repair method 
instead.

Costs of Compliance

    The FAA estimates that this AD affects 625 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Cost per        Cost on U.S.
            Action                    Labor cost             Parts cost           airplane          operators
----------------------------------------------------------------------------------------------------------------
Inspect the stabilator tip      0.5 work-hour x $85     Not applicable......  $42.50 per        $26,562.50 per
 tube and weight assembly.       per hour = $42.50.                            inspection        inspection
                                                                               cycle.            cycle.
Inspect the stabilator tip      0.5 work-hour x $85     Not applicable......  $42.50..........  $26,562.50.
 ribs.                           per hour = $42.50.
Replace the stabilator tab      4 work-hours x $85 per  $817................  $1,157..........  $723,125.
 forward rib/horn assemblies.    hour = $340.
Install additional nose ribs..  1 work-hour x $85 per   $367................  $452............  $282,500.
                                 hour = $85.
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    The FAA estimates the following costs to do any necessary repairs 
or replacements that will be required based on the results of the 
inspection. The FAA has no way of determining the number of airplanes 
that might need these repairs or replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                Action                         Labor cost                   Parts cost               airplane
----------------------------------------------------------------------------------------------------------------
Repair stabilator tip tube and weight   4 work-hours x $85 per    $80...........................            $420
 assemblies (airplanes without kit P/N   hour = $340.
 763 987).
Install missing stabilator tip rib      1 work hour x $85 per     $39...........................             124
 rivets and/or the stabilator tip tube   hour = $85.
 and weight assembly attachment screws.
Balance stabilator....................  5 work-hours x $85 per    Not applicable................             425
                                         hour = $425.
----------------------------------------------------------------------------------------------------------------

    For airplanes with kit P/N 763 987, the cost to repair cracking may 
vary significantly from airplane to airplane, and therefore the FAA has 
no way of determining an estimated cost.

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.
    The FAA is 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) Will not affect intrastate aviation in Alaska, and
    (3) 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 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:
0
a. Removing Airworthiness Directive 78-02-03 [Reg. Docket No. 77-EA-81, 
Amendment 39-3128] (43 FR 3079, January 23, 1978); and
0
b. Adding the following new airworthiness directive:

2021-25-11 Piper Aircraft, Inc.: Amendment 39-21855; Docket No. FAA-
2020-1006; Project Identifier 2019-CE-047-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective January 25, 2022.

(b) Affected ADs

    This AD replaces AD 78-02-03 [Reg. Docket No. 77-EA-81, 
Amendment 39-3128] (43 FR 3079, January 23, 1978) (AD 78-02-03).

(c) Applicability

    This AD applies to Piper Aircraft, Inc., Model PA-23-250 
airplanes, serial numbers 27-7654001 through 27-7954121, 
certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 5510, Horizontal 
Stabilizer Structure.

(e) Unsafe Condition

    This AD was prompted by reports of cracks developing on the 
stabilator structure. The FAA is issuing this AD to prevent 
weakening of the stabilator structure and to detect and

[[Page 72188]]

correct cracks on the stabilator tip tube and weight assembly. The 
unsafe condition, if not addressed, could cause weakening of the 
complete structure and lead to loss of the trim tab and counter 
balance weight, which may result in reduced airplane control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Previously Required Actions Retained From AD 78-02-03

    (1) Within 50 hours time-in-service (TIS) after January 26, 1978 
(the effective date of AD 78-02-03), do the following inspections 
and modifications.
    (i) For airplanes with serial numbers 27-7654001 through 27-
7754054, inspect both stabilator tip ribs for missing rivets and 
missing tube and weight assembly attachment screws and if necessary 
alter in accordance with Piper Service Bulletin (SB) 547, dated 
March 1, 1977.
    (ii) For airplanes with serial numbers 27-7654001 through 27-
7754127, 27-7754130, 27-7754131, 27-7754133 through 27-7754136, and 
27-7754138 through 27-7754144, replace the right and left stabilator 
tab forward inboard rib/horn assemblies by installing Piper Kit 761 
143 or equivalent kit in accordance with Piper SB 569, dated August 
24, 1977.
    (iii) For airplanes with serial numbers 27-7654001 through 27-
7754041 equipped with stabilators Piper part number (P/N) 15658-2, 
15658-3, 15658-22 or 15658-23, reinforce the mounting of the 
stabilator tube and weight assemblies by installing additional nose-
ribs with Piper Kit 761 141 or equivalent kit in accordance with 
Piper Service Letter 807A, dated September 8, 1977.
    (2) Before further flight after completing the alterations in 
paragraphs (g)(1)(ii) and (iii) of this AD, balance the stabilator.

(h) Inspection of Stabilator Tip Tube and Weight Assembly

    Within 10 hours TIS after the effective date of this AD or 
within 100 hours TIS after completing the last inspection required 
by paragraph (a) of AD 78-02-03, whichever occurs later, and 
thereafter at intervals not to exceed 100 hours TIS, inspect the 
left and right stabilator balance weight assemblies for cracks and 
complete any necessary repairs by following Parts I and II of the 
Instructions in Piper SB No. 540B, dated February 9, 2021, except 
you are not required to contact Piper for repair instructions. 
Instead, repair in accordance with FAA-approved procedures.

(i) Credit for Previous Actions

    You may take credit for the initial inspection and corrective 
actions required by paragraph (h) of this AD if you performed those 
actions before the effective date of this AD using Piper SB No. 540, 
dated January 4, 1977, or SB No. 540A, dated October 20, 1980.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta ACO Branch, 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 certification office, 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.
    (3) For service information that contains steps that are labeled 
as Required for Compliance (RC), the following provisions 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.

(k) Related Information

    For more information about this AD, contact John Marshall, 
Aviation Safety Engineer, Atlanta ACO Branch, FAA, 1701 Columbia 
Avenue, College Park, GA 30337; phone: (404) 474-5524; fax: (404) 
474-5605; email: [email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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 Service Bulletin No. 547, dated March 1, 1977.
    (ii) Piper Service Bulletin No. 569, dated August 24, 1977.
    (iii) Piper Service Letter No. 807A, dated September 8, 1977.
    (iv) Piper Service Bulletin No. 540B, February 9, 2021.
    (3) For the service information identified in this AD, contact 
Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, FL 32960; phone: 
(772) 299-2141; website: https://www.piper.com/.
    (4) You may view this referenced service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 901 
Locust, Kansas City, MO 64106. For information on the availability 
of this material at the FAA, call (817) 222-5110.
    (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, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on December 3, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-27510 Filed 12-20-21; 8:45 am]
BILLING CODE 4910-13-P