FR Doc 03-29871

[Federal Register: December 3, 2003 (Volume 68, Number 232)]
[Rules and Regulations]
[Page 67588-67590]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03de03-2]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-03-AD; Amendment 39-13376; AD 2003-24-07]
RIN 2120-AA64

Airworthiness Directives; The New Piper Aircraft, Inc. Models PA-
31, PA-31-300, PA-31-325, PA-31-350, PA-31P, PA-31T, PA-31T1, PA-31T2,
PA-31T3, and PA-31P-350 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to all The New Piper Aircraft, Inc. (Piper) Models PA-31, PA-
31-300, PA-31-325, PA-31-350, PA-31P, PA-31T, PA-31T1, PA-31T2, PA-
31T3, and PA-31P-350 airplanes. This AD requires you to install an
inspection hole (or use for inspection the tooling hole in the rudder
bottom rib), conduct a detailed visual inspection of the rudder torque
tube and associated ribs for corrosion, and, if corrosion is found,
replace or repair the rib/rudder torque tube assembly. This AD is the
result of reports of rudder tube corrosion. The actions specified by
this AD are intended to detect and correct corrosion in the rudder
torque tube assembly and rudder rib, which could result in failure of
the rudder torque tube. This failure could lead to loss of rudder
control.

DATES: This AD becomes effective on February 9, 2004.
As of February 9, 2004, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.

ADDRESSES: You may get the service information referenced in this AD
from The New Piper Aircraft, Inc., Customer Services, 2926 Piper Drive,
Vero Beach, Florida 32960; telephone: (772) 567-4361; facsimile: (772)
978-6584.
You may view this information at the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2003-CE-03-AD, 901 Locust, Room 506, 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: William O. Herderich, Aerospace
Engineer, FAA, Atlanta Aircraft Certification Office, One Crown Center,
1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; telephone:
(770) 703-6082; facsimile: (770) 703-6097.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD? The FAA has received several
reports of rudder tube and rib corrosion on Piper PA-31 Series
airplanes. The area surrounding the rudder torque tube assembly and
rudder rib does not have a means or access to inspect in this area and
neither means nor exits for water to drain out.
What is the potential impact if FAA took no action? Corrosion in
the rudder torque tube assembly and rudder rib could result in failure
of the rudder torque tube. This failure could lead to loss of rudder
control.
Has FAA taken any action to this point? We issued a proposal to
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to
include an AD that would apply to all Piper Models PA-31, PA-31-300,
PA-31-325, PA-31-350, PA-31P, PA-31T, PA-31T1, PA-31T2, PA-31T3, and
PA-31P-350 airplanes. This proposal was published in the Federal
Register as a notice of proposed rulemaking (NPRM) on June 3, 2003 (68
FR 33030). The NPRM proposed to require you to install an inspection
hole, conduct a detailed visual inspection of the rudder torque tube
and associated ribs for corrosion, and, if corrosion is found, replace
the rib/rudder torque tube assembly.

Comments

Was the public invited to comment? We provided the public the
opportunity to participate in the development of this AD. The following
presents the comments received on the proposal and FAA's response to
each comment:

Comment Issue No. 1: Extend the Compliance Time

What is the commenter's concern? A commenter recommends extending
the compliance time from 100 hours time-in-service (TIS) to 150 hours
TIS. The commenter states that the extension is necessary due to a
reported lack of parts and the difficulty in scheduling involved with
AD compliance.
What is FAA's response to the concern? The FAA agrees that 150
hours TIS would be a more realistic compliance time.
We are changing the final rule AD action accordingly.

Comment Issue No. 2: Allow Option to Repair Parts

What is the commenter's concern? The commenter recommends the
following: if you find ``light corrosion'' or ``corrosion that could
significantly weaken the rib/rudder torque tube assembly that is less
than 50 percent of the thickness over an area less than two square
inches' then you may clean up, repair, and coat the corroded area to
prevent further damage and continue the part in service.
What is FAA's response to the concern? The FAA is currently unaware
of any approved repair design for the rib/rudder torque tube assembly.
However, FAA has no objection to operation of aircraft with parts that
have been repaired or reworked per an FAA-approved repair design.
Therefore, we are changing the final rule AD action to provide the
option of repairing with an FAA-approved design.

Comment Issue No. 3: Special Flight Permits Are Not Addressed in the
NPRM

What is the commenter's concern? The commenter states that since
special flight permits are not addressed in the NPRM, the current 14
CFR part 39 applies and that there is no restriction against issuing a
special flight permit.
What is FAA's response to the concern? On July 10, 2002, the FAA
published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002),
which governs the FAA's AD system. This regulation now includes
material that

[[Page 67589]]

relates to special flight permits. This material previously was
included in each individual AD. Since this material is included in 14
CFR part 39, we did not include it in this AD action.
We are not making any changes to the final rule AD action.

Comment Issue No. 4: Allow an Alternate Method of Inspection

What is the commenter's concern? The commenter suggests an
alternative to installing an inspection hole in the rudder skin for the
rudder torque tube assembly. This alternative method of inspection is
to use the tooling hole in the rudder bottom rib since this is
convenient and does not contribute to corrosion. Further, you could
enlarge the tooling hole to ease use of inspection tools.
What is FAA's response to the concern? The FAA agrees that the
proposed alternative use of the tooling hole (with optional
enlargement) in the rudder bottom rib is an acceptable substitute to
installing an access hole.
We are changing the final rule AD action accordingly.

Comment Issue No. 5: Allow Application of Corrosion Inhibitor

What is the commenter's concern? The commenter recommends allowing
application of rust inhibitor compound.
What is FAA's response to the concern? The application of rust
inhibitor compound to the contact surfaces is identified in Piper
Service Bulletin No. 1105A, dated September 22, 2003. As a minor
correction, we are also noting to protect bare metal per Section 8, FAA
Advisory Circular (AC) 43.13-1B.
We are incorporating the referenced correction in the final rule AD
action.

Conclusion

What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for the
changes discussed above and minor editorial corrections. We have
determined that these changes and minor corrections:

--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.

Changes to 14 CFR Part 39--Effect on the AD

How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. This material
previously was included in each individual AD. Since this material is
included in 14 CFR part 39, we will not include it in future AD
actions.

Costs of Compliance

How many airplanes does this AD impact? We estimate that this AD
affects 2,269 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes?
We estimate the following costs to accomplish the installation of
inspection and drain holes and inspection of torque tube and associated
ribs for corrosion:

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Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
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3 workhours x $60 per hour = $180. $10 $190 2,269 x $190 = $431,110
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We estimate the following costs to accomplish any necessary
corrosion repairs/replacements of the rib/torque tube assembly that
would be required based on the results of this proposed inspection. We
have no way of determining the number of airplanes that may need this
repair/replacement:

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Total cost per
Labor cost Parts cost airplane
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16 workhours x $60 per hour = $960 $800 $1,760
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Regulatory Findings

Will this AD impact various entities? We have determined that 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.
Will this AD involve a significant rule or regulatory action? 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 the 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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``2003-CE-03-AD'' in your request.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under 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

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. FAA amends Sec. 39.13 by adding a new AD to read as follows:

[[Page 67590]]

2003-24-07 The New Piper Aircraft, Inc.: Amendment 39-13376; Docket
No. 2003-CE-03-AD.

When Does This AD Become Effective?

(a) This AD becomes effective on February 9, 2004.

What Other ADs Are Affected by This Action?

(b) None.

What Airplanes Are Affected by This AD?

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Model Serial numbers
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PA-31, PA-31-300, PA-31-325............... 31-2 through 31-8312019
PA-31-350................................. 31-5001 through 31-8553002
PA-31P.................................... 31P-1 through 31P-7730012
PA-31P-350................................ 31P-8414001 through 31P-
8414050
PA-31T.................................... 31T-7400001 through 31T-
8120104
PA-31T1................................... 31T-7804001 through 31T-
1104017
PA-31T2................................... 31T-8166001 through 31T-
1166008
PA-31T3................................... 31T-8275001 through 31T-
5575001
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What Is the Unsafe Condition Presented in This AD?

(d) This AD is the result of reports of rudder tube corrosion.
The actions specified by this AD are intended to detect and correct
corrosion in the rudder torque tube assembly and rudder rib, which
could result in failure of the rudder torque tube. This failure
could lead to loss of rudder control.

What Must I Do to Address This Problem?

(e) To address this problem, you must accomplish the following:

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Actions Compliance Procedures
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(1) Install an inspection hole Within the next Install an
in the rudder skin for the 150 hours time-in- inspection hole
rudder torque tube assembly; OR service (TIS) per The New Piper
instead of installing an after February 9, Aircraft, Inc.
inspection hole, use the 2004 (the Service Bulletin
tooling hole in the rudder effective date of No. 1105A, dated
bottom rib. You may enlarge the this AD), unless September 22,
diameter of the tooling hole no already 2003. Protect
more than 0.25 inches to accomplished. bare metal per
facilitate inspection and Section 8, FAA
corrosion treatment. Advisory Circular
(AC) 43.13-1B.
(2) Visually inspect the rudder Before further Follow The New
torque tube and associated ribs flight after the Piper Aircraft,
for corrosion. installation Inc. Service
required in Bulletin No.
paragraph (e)(1) 1105A, September
of this AD and 22, 2003.
thereafter at
intervals not to
exceed 12
calendar months.
(3) If you find corrosion Before further Follow The New
damage:. flight after any Piper Aircraft,
(i) Replace the rib/rudder inspection Inc. Service
torque assembly; OR. required in Bulletin No.
(ii) Repair the damaged torque paragraph (e)(2) 1105A, dated
tube using an FAA-approved of this AD where September 22,
repair design. corrosion damage 2003. Repairs
is found. must address
items in
paragraph (f) of
this AD and may
be approved per
FAA Order 8300.10
(Volume 2,
Chapter 1),
Airworthiness
Inspector's
Handbook.
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(f) All repairs must address the following:
(1) Detect hidden corrosion damage:
(i) In the faying surface between the rudder ribs and torque
tube assembly attachments.
(ii) Inside the bore of the torque tube.
(2) Establish procedures for removing corrosion or for corrosion
prevention of repaired parts. Advisory Circular (AC) 43.13-1B
Acceptable Methods, Techniques, and Practices-Aircraft Inspection
and Repair, and AC 43-4A, Corrosion Control for Aircraft, provide
resources for establishment of these procedures.
(3) For repairs involving material removal without
reinforcement: Define a clear, accurate, and complete description of
negligible damage limits. Note that acceptable amounts of material
removal may be location-dependent. Higher-stressed areas will be
less tolerant of material removal.
(4) For all repairs involving reinforcement: A clear, accurate,
and complete description of the repair design must be established
per 14 CFR part 21.31.
(5) Verify that all repairs follow Subpart C--Strength
Requirements and Subpart D--Design and Construction of Civil
Aviation Regulations (CAR) 3, dated May 15, 1956 (the original
certification basis for the Piper PA-31 Series as shown in type
certificate data sheets A8EA and A20SO).

May I Request an Alternative Method of Compliance?

(g) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.13. Send your request to the Manager, Atlanta Aircraft
Certification Office (ACO), FAA. For information on any already
approved alternative methods of compliance, contact William O.
Herderich, Aerospace Engineer, FAA, Atlanta ACO, One Crown Center,
1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349;
telephone: (770) 703-6082; facsimile: (770) 703-6097.

Does This AD Incorporate Any Material by Reference?

(h) You must do the actions required by this AD following the
instructions in The New Piper Aircraft, Inc. Service Bulletin No.
1105A, dated September 22, 2003. The Director of the Federal
Register approved the incorporation by reference of this service
bulletin per 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy
from The New Piper Aircraft, Inc., Customer Services, 2926 Piper
Drive, Vero Beach, Florida 32960; telephone: (772) 567-4361;
facsimile: (772) 978-6584. You may review copies at FAA, Central
Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas
City, Missouri 64106; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.

Issued in Kansas City, Missouri, on November 24, 2003.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-29871 Filed 12-2-03; 8:45 am]

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