[Federal Register Volume 61, Number 200 (Tuesday, October 15, 1996)]
[Rules and Regulations]
[Pages 53611-53613]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-26047]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-CE-84-AD; Amendment 39-9780; AD 96-21-03]
RIN 2120-AA64


Airworthiness Directives; The New Piper Aircraft, Inc. PA31, 
PA31P, PA31T, and PA42 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to The New Piper Aircraft, Inc. (Piper) PA31, PA31P, PA31T, and 
PA42 series airplanes. This action requires inspecting for cracks 
beneath and in the area of the inboard aileron hinge bracket on the 
aileron spar and rib using dye penetrant methods, replacing any cracked 
aileron spar or rib, and replacing the inboard aileron hinge bracket 
with a hinge bracket of improved design. Several reports of cracks in 
the vicinity of the inboard aileron hinge bracket, aileron spar, and 
aileron rib prompted this proposed action. The actions specified by the 
proposed AD are intended to prevent structural failure of the aileron 
caused by cracks in the area of the inboard aileron hinge bracket, 
which, if not detected and corrected, could result in loss of control 
of the airplane.

DATES: Effective December 10, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 10, 1996.

ADDRESSES: Service information that applies to this AD may be obtained 
from The New Piper Aircraft, Inc., Attn: Customer Service, 2926 Piper 
Dr., Vero Beach, Florida, 32960. This information may also be examined 
at the Federal Aviation Administration (FAA), Central Region, Office of 
the Assistant Chief Counsel, Attention: Rules Docket 95-CE-84-AD, Room 
1558, 601 E. 12th Street, Kansas City, Missouri 64106; or at the Office 
of the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Christina Marsh, Aerospace Engineer, 
FAA, Atlanta Aircraft Certification Office, Campus Building, 1701 
Columbia Avenue, suite 2-160, College Park, Georgia 30337-2748; 
telephone (404) 305-7362; facsimile (404) 305-7348.

SUPPLEMENTARY INFORMATION:

Events Leading to This Action

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to Piper PA31, PA31P, 
PA31T, and PA42 series airplanes was published in the Federal Register 
on March 27, 1996 (61 FR 13468). The action proposed to require:

--inspecting the aileron spar beneath and in the area of the inboard 
aileron hinge bracket for cracks;
--if cracks are found in the area of the aileron spar, inspecting the 
aileron rib for cracks, and replacing the cracked spar assembly and any 
cracked rib;
--replacing the inboard aileron hinge brackets with part number (P/N) 
74461-02 (left) and P/N 74461-03 (right).

Related Service Information

    Accomplishment of the proposed action would be in accordance with 
Piper Service Bulletin (SB) No. 967, dated January 24, 1994 or Piper SB 
No. 974, dated October 19, 1994.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received.
    The first commenter recommends that the AD state specifically that 
prior compliance with the applicable service bulletin (SB) be 
considered compliance with the requirements of the AD. The commenter 
has complied with Piper SB 974 and adds that paragraph (a) should only 
be required on aircraft that have not installed the redesigned aileron 
hinge brackets. The commenter continues to state that paragraph (a) as 
presently worded may be interpreted to require inspection of the 
aileron spar on all affected aircraft regardless of the part number (P/
N) of the inboard hinge installed on the aircraft.
    The FAA concurs that additional clarification is justified. The 
inspection of the aileron spar is intended to be required for aircraft 
that have not previously installed P/N 74461-02 (left) and P/N 74461-03 
(right) inboard hinges. The ``Applicability'' section in the AD will be 
changed to state, ``The following airplane models and serial numbers 
that are not equipped with part number (P/N) 74461-02 (left) and P/N 
74461-03 (right) inboard aileron hinge brackets, certificated in any 
category.''
    The second commenter recommends that the AD be applicable to 
aircraft with greater than 3,000 hours time-in-service (TIS). This 
commenter operates Piper airplane Models PA-31-350, a PA-31, and a PA-
31P with 11,000, 8,600 and 2,000 hours TIS respectively, and states 
that based on their fleet experience, cracking is most likely to appear 
at or after 3,000 hours TIS and recommends the 3,000 hour TIS as the 
threshold for this AD.
    The FAA concurs and points out that the proposed action already 
proposes what the commenter is recommending. The compliance time as 
proposed specifies compliance ``upon the accumulation of 3,000 hours 
TIS, or within the next 100 hours TIS, whichever occurs later.''

[[Page 53612]]

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections and the clarification of the 
``Applicability'' section. The FAA has determined that these minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.

Cost Impact

    The FAA estimates that 2,501 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 7 workhours per 
airplane to accomplish the required action, and that the average labor 
rate is approximately $60 an hour. Parts cost $300 per airplane. Based 
on these figures, the total cost impact for the initial inspection and 
the modification required by this AD on U.S. operators is estimated to 
be $1,800,720 or $720 per airplane. This figure does not include the 
amount for repetitive inspections and is based on the assumption that 
all of the owners/operators of the affected airplanes have not 
inspected for cracks, repaired cracks, or incorporated the modification 
of this AD. The FAA has no way of determining the number of repetitive 
inspections each owner/operator will incur before the modification is 
accomplished.
    Piper has informed the FAA that parts have been distributed to 
equip approximately 1,250 airplanes. Assuming that these distributed 
parts are incorporated on the affected airplanes, the cost of the AD 
would be reduced by $900,000 from $1,800,720 to $900,720.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (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); 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. A copy of the final evaluation prepared for this 
action is contained in the Rules Docket. A copy of it may be obtained 
by contacting the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
(AD) to read as follows:

96-21-03  The New Piper Aircraft, Inc. : Amendment 39-9780; Docket 
No. 95-CE-84-AD.

    Applicability: The following airplane models and serial numbers 
that are not equipped with part number (P/N) 74461-02 (left) and P/N 
74461-03 (right) inboard aileron hinge brackets, certificated in any 
category:

------------------------------------------------------------------------
                 Models                            Serial Nos.          
------------------------------------------------------------------------
 The following aircraft should reference Piper Service Bulletin No. 974,
                         dated October 19, 1994                         
                                                                        
------------------------------------------------------------------------
PA31, PA31-300, and PA31-325...........  31-2 through 31-8312019.       
PA31-350...............................  31-5001 through 31-8553002.    
PA31P-350..............................  31P-8414001 through 31P-       
                                          8414050.                      
PA31T3.................................  31T-8275001 through 31T-       
                                          8475001, and 31T-5575001.     
                                                                        
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 The following aircraft should reference Piper Service Bulletin No. 967,
                         dated January 24, 1994                         
                                                                        
------------------------------------------------------------------------
PA31P..................................  31P-1 through 31P-7730012, and 
                                          31P-03.                       
PA31T..................................  31T-7400002 through 31T-       
                                          7400009, and 31T-7520001      
                                          through 31T-8120104.          
PA31T1.................................  31T-7804001 through 31T-       
                                          8304003, and 31T-1104004      
                                          through 31T-1104017.          
PA31T2.................................  31T-8166001 through 31T-       
                                          8166076, and 31T-1166001      
                                          through 31T-1166008.          
PA42...................................  42-7800001 through 42-7800004, 
                                          and 42-8001001 through 42-    
                                          8001106.                      
PA42-720...............................  42-8301001, 42-8301002, 42-    
                                          5501003 through 42-5501023, 42-
                                          5501025 through 42-5501027, 42-
                                          5501029 through 42-5501031, 42-
                                          5501033, and 42-5501039       
                                          through 42-5501059.           
PA42-720R..............................  42-5501024, 42-5501028, 42-    
                                          5501032, and 42-5501034       
                                          through 42-5501038.           
PA42-1000..............................  42-5527002 through 42-5527044. 
------------------------------------------------------------------------

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (e) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not?
    Compliance: Upon the accumulation of 3,000 hours time-in-service 
(TIS), or within the next 100 hours TIS after the effective date of 
this AD, whichever occurs later, unless already accomplished.

    Note 2: The paragraph structure of this AD is as follows:

Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.

Level 2 and Level 3 structures are designations of the Level 1 
paragraph they immediately follow.
    To prevent structural failure of the aileron caused by cracks in 
the area of the inboard aileron hinge bracket, which, if not 
detected and corrected, could result in loss of control of the 
airplane, accomplish the following:
    (a) Inspect (using dye penetrant methods) the area beneath and 
in the area of the inboard aileron hinge bracket on the aileron spar 
for cracks in accordance with the INSTRUCTIONS section of Piper 
service bulletin (SB) No. 967, dated January 24, 1994, or Piper SB 
No. 974, dated October 19, 1994, whichever service bulletin applies 
to the particular model and serial number.
    (1) If cracks are found on the aileron spar:
    (i) Prior to further flight, inspect the corresponding aileron 
rib at the inboard aileron hinge bracket location;

[[Page 53613]]

    (ii) Prior to further flight, replace any cracked spar assembly 
and any cracked aileron rib in accordance with the applicable 
Maintenance Manual;
    (iii) Prior to further flight, replace the inboard aileron hinge 
brackets with an inboard aileron hinge bracket of improved design, 
part number (P/N) 74461-02 (left) and P/N 74461-03 (right), in 
accordance with the INSTRUCTIONS section of Piper SB No. 967, dated 
January 24, 1994, or Piper SB No. 974, dated October 19, 1994, as 
applicable.
    (2) If no cracks are found, prior to further flight, replace the 
inboard aileron hinge brackets with a part of improved design P/N 
74461-02 (left) and P/N 74461-03 (right), in accordance with the 
INSTRUCTIONS section of Piper SB No. 967, dated January 24, 1994, or 
Piper SB No. 974, dated October 19, 1994, as applicable.
    (b) If the inboard aileron hinge brackets, P/N 74461-02 (left) 
or P/N 74461-03 (right) have been ordered from the manufacturer but 
are not available, prior to further flight, and thereafter at 
intervals not to exceed 100 hours TIS, dye penetrant inspect beneath 
and in the vicinity of the inboard aileron hinge bracket for cracks 
in accordance with the INSTRUCTIONS section of Piper SB No. 967, 
dated January 24, 1994, or Piper SB No. 974, dated October 19, 1994, 
as applicable.
    (c) If any one of the following occurs, prior to further flight, 
terminate the above repetitive inspections, replace any cracked 
aileron rib and any cracked spar assembly (if applicable), and 
replace the inboard aileron hinge bracket as specified in paragraph 
(a)(1)(iii) of this AD:
    (1) Parts become available;
    (2) An inboard aileron bracket hinge, aileron spar or aileron 
rib is found cracked; or
    (3) 1,000 hours TIS are accumulated after the initial inspection 
required by this AD.
    (d) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.
    (e) An alternative method of compliance or adjustment of the 
initial or repetitive compliance times that provides an equivalent 
level of safety may be approved by the Manager, FAA, Atlanta 
Aircraft Certification Office, Campus Building, 1701 Columbia 
Avenue, suite 2-160, College Park, Georgia 30337-2748. The request 
shall be forwarded through an appropriate FAA Maintenance Inspector, 
who may add comments and then send it to the Manager, Atlanta 
Aircraft Certification Office.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta Aircraft Certification Office.

    (f) The inspections and replacements required by this AD shall 
be done in accordance with Piper. Service Bulletin No. 967, dated 
January 24, 1994, or Piper. Service Bulletin No. 974, dated October 
19, 1994. This incorporation by reference was approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Copies may be obtained from The New Piper 
Aircraft, Inc., Attn: Customer Service, 2926 Piper Dr., Vero Beach, 
Florida, 32960. Copies may be inspected at the FAA, Central Region, 
Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th 
Street, Kansas City, Missouri, or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (g) This amendment (39-9780) becomes effective on December 10, 
1996.

    Issued in Kansas City, Missouri, on October 4, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-26047 Filed 10-11-96; 8:45 am]
BILLING CODE 4910-13-U