Airworthiness Directives; Fairchild Aircraft Models SA227-AC and SA227-AT Airplanes

DEPARTMENT OF TRANSPORTATION

14 CFR Part 39

[Docket No. 91-CE-12-AD; Amendment 39-9118; AD 95-01- 07]

Airworthiness Directives; Fairchild Aircraft Models SA227-AC and

SA227-AT Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes Airworthiness Directive (AD) 83-12-

01, which currently requires repetitively inspecting the lower wing

skin panel for cracks on certain Fairchild Aircraft Models SA227-AC and

SA227-AT airplanes, and installing wing skin reinforcement doublers if

any wing skin crack is found. The Federal Aviation Administration's

policy on aging commuter-class aircraft is to eliminate, or, in certain

instances, reduce the number of certain repetitive short-interval

inspections when improved parts or modifications are available. This

action requires installing wing skin reinforcement doublers or wing

skin stringer ties as terminating action for the repetitive inspections

that are currently required by AD 83-12-01. The actions specified by

this AD are intended to prevent fatigue failure of the lower wing skin

panels, which could result in loss of control of the airplane.

DATES: Effective February 17, 1995.

The incorporation by reference of certain publications listed in

the regulations is approved by the Director of the Federal Register as

of February 17, 1995.

ADDRESSES: Service information that applies to this AD may be obtained

from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-

0490; telephone (210) 824-9421. This information may also be examined

at the Federal Aviation Administration (FAA), Central Region, Office of

the Assistant Chief Counsel, 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: Mr. Hung Viet Nguyen, Aerospace

Engineer, FAA, Airplane Certification Office, 2601 Meacham Boulevard,

Fort Worth, Texas 76193-0150; telephone (817) 222-5155; facsimile (817)

222-5959.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to include an AD that would apply

to certain Fairchild Aircraft Models SA227-AC and SA227-AT airplanes

was published in the Federal Register on March 30, 1994 (59 FR 14797).

The action proposed to supersede AD 83-12- 01 with a new AD that would

(1) retain the requirement of repetitively inspecting the lower wing

skin panel, and installing wing skin reinforcement doublers if any wing

skin crack is found; and (2) require either installing wing skin

reinforcement doublers or wing skin stringer ties as terminating action

for the repetitive inspections. The proposed actions would be

accomplished in accordance with Fairchild SB No. 227-57- 002, Issued:

June 6, 1983, Revised: January 23, 1984.

Interested persons have been afforded an opportunity to participate

in the making of this amendment. No comments were received on the

proposed rule or the FAA's determination of the cost to the public.

After careful review of all available information, the FAA has

determined that air safety and the public interest require the adoption

of the rule as proposed except for minor editorial corrections. The FAA

has determined that these minor corrections will not change the meaning

of the AD nor add any additional burden upon the public than was

already proposed.

This action is based on the FAA's aging commuter-class airplane

policy, which briefly states that owners/operators in commuter service

should incorporate modifications or install improved parts when the

modification or installation would eliminate, or, in certain instances,

reduce a repetitive inspection on a critical structure.

The FAA estimates that 125 airplanes in the U.S. registry will be

affected by this AD, that it will take approximately 9 workhours per

airplane to accomplish the required action if reinforcement doublers

were installed (1 workhour/inspection and 8 workhours/modification) or

25 workhours per airplane to accomplish the required action if wing

skin stringer ties were installed (1 workhour/inspection and 24

workhours/modification), and that the average labor rate is

approximately $55 an hour. Parts cost approximately $56 per airplane

for the wing skin reinforcement doublers and $179 per airplane for the

wing skin stringer ties. Based on these figures, the total cost impact

of this AD on U.S. operators is estimated to be either $68,875 for

those airplane operators incorporating the reinforcement doubler

modification or $194,250 for those airplane operators utilizing the

wing skin stringer ties modification. This cost figure is based on the

assumption that no affected airplane owner/operator has accomplished

one of the required inspection-terminating modifications. The figure

does not include repetitive inspection costs. The FAA has no way of

determining how many repetitive inspections each owner/operator may

incur.

The intent of the FAA's aging commuter airplane program is to

ensure safe operation of commuter-class airplanes that are in

commercial service without adversely impacting private operators. Of

the approximately 125 [[Page 2496]] airplanes in the U.S. registry that

will be affected by this AD, approximately 76 are operated in scheduled

passenger service. A significant number of the remaining 49 airplanes

are operated in other forms of air transportation such as air cargo and

air taxi.

This AD allows 500 hours time-in-service (TIS) before mandatory

accomplishment of the design modification. The average utilization of

the fleet for those airplanes in commercial commuter service is

approximately 25 to 50 hours TIS per week. Based on these figures,

operators of commuter-class airplanes involved in commercial operation

will have to accomplish the required modification within 2 to 5

calendar months after this AD becomes effective. For private owners,

who typically operate between 100 to 200 hours TIS per year, this

allows 2 to 5 calendar years before the required modification will be

mandatory.

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 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.

106(g); and 14 CFR 11.89.

Sec. 39.13 [Amended]

2. Section 39.13 is amended by removing AD 83-12-01, Amendment 39-

4693, and by adding a new AD to read as follows:

95-01-07 Fairchild Aircraft: Amendment 39-9118; Docket No. 91-CE-12-

AD. Supersedes AD 83-12-01, Amendment 39-4693.

Applicability: The following model and serial number airplanes,

certificated in any category:

------------------------------------------------------------------------

Model Serial Nos.

------------------------------------------------------------------------

SA227-AC............................. 415, 416, and 420 through 554.

SA227-AT............................. 423 through 554.

------------------------------------------------------------------------

Compliance: Required as indicated in the body of this AD, unless

already accomplished.

To prevent fatigue failure of the lower wing skin panels, which

could result in loss of control of the airplane, accomplish the

following:

(a) Within the next 50 hours time-in-service (TIS) after the

effective date of this AD, unless already accomplished (compliance

with AD 83-12-01), dye penetrant inspect the lower wing skin panel

of both wings in the area of Wing Station (WS) 187.0 in accordance

with paragraph IIA of the ACCOMPLISHMENT INSTRUCTIONS section of

Fairchild Service Bulletin (SB) 227-57-002, Issued: June 6, 1983,

Revised: January 23, 1984.

(1) If cracks are found, prior to further flight, install

reinforcement doublers, part number 27K31013-001 LH and 27K31013-002

RH, in accordance with paragraph IIB of the ACCOMPLISHMENT

INSTRUCTIONS section of Fairchild SB 227-57-002, Issued: June 6,

1983, Revised: January 23, 1984.

(2) If no cracks are found, reinspect thereafter at intervals

not to exceed 50 hours TIS until the modification specified in

paragraph (b) of this AD is accomplished.

(b) Within the next 500 hours TIS after the effective date of

this AD, unless already accomplished as specified in paragraph

(a)(1) of this AD, accomplish one of the following on both wings:

(1) Install reinforcement doublers, part number 27K31013-001 LH

and 27K31013-002 RH, in accordance with paragraph IIB of the

ACCOMPLISHMENT INSTRUCTIONS section of Fairchild SB 227-57-002,

Issued: June 6, 1983, Revised: January 23, 1984; or

(2) Install stringer ties, P/N 27-13869, in accordance with

paragraph IIC of the ACCOMPLISHMENT INSTRUCTIONS section of

Fairchild SB 227-57-002, Issued: June 6, 1983, Revised: January 23,

1984.

(c) Incorporating (on both wings) the modification specified in

paragraph (a)(1), (b)(1) or (b)(2) of this AD terminates the

repetitive inspection requirement of this AD.

(d) Special flight permits may be issued in accordance with

Secs. 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, Airplane

Certification Office (ACO), 2601 Meacham Boulevard, Fort Worth,

Texas 76193-0150. The request shall be forwarded through an

appropriate FAA Maintenance Inspector, who may add comments and then

send it to the Manager, Fort Worth ACO.

Note: Information concerning the existence of approved

alternative methods of compliance with this AD, if any, may be

obtained from the Fort Worth ACO.

(f) The inspections and installation required by this AD shall

be done in accordance with Fairchild Service Bulletin 227-57-002,

Issued: June 6, 1983, Revised: January 23, 1984. 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 Fairchild Aircraft, P.O. Box 790490, San Antonio,

Texas 78279-0490. 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 (39-9118) supersedes AD 83-12-01, Amendment

39-4693.

(h) This amendment (39-9118) becomes effective on February 17,

1995.

Issued in Kansas City, Missouri, on January 4, 1995.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 95-517 Filed 1-9-95; 8:45 am]

BILLING CODE 4910-13-M