Air Safety Week: Significant Regulatory Activity

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Significant Regulatory Activity

Attempts thus far to resolve the ongoing CRJ100/200 flap failure problem has led to manufacturer Bombardier endorsing an interim fix while at the same time engaging an airframe expert (US manufacturer Eaton) to design a permanent fix (see acc&inc table 14 Jan entry for Flt SKW5808 flap failure). SkyWest has indicated it has experienced "some challenges and difficulty" in implementing the flap fix currently available, as called out in the Airworthiness Directive (i.e. to clean, lubricate, calibrate, seal and test at a cost of $2,160 per regional jet). The AD had a target date for operator implementation of 03 Jan. The regulator in October 2007 proposed amending the August AD on CRJ100/200 flaps to include requirements that operators of the type in the USA provide simulator training covering reduced- or zero-flap landings for pilots, and perform several additional maintenance actions. It's generally acknowledged that moisture ingress during cold weather operations is the nub of the problem. According to Bombardier, Eaton's design modification task, set to begin soon, is being done "in the spirit of continuous improvement" and should enhance reliability - particularly for cold weather operations.

The FAA recently certified ARINC Incorporated to issue aircraft STCs and perform STC-related aircraft service and modification work under the FAA's new Organization Designation Authorization (ODA) program. This New FAA Certification Program will ultimately replace the DAS System (Designated Alteration Station). ODA rules permit a greater delegation of functions related to engineering, manufacturing, operations, airworthiness, and maintenance. In addition to STC designees, DOA, SFAR36, PC ODAR, PMA ODAR, and Operator/145 ODAR designees will be required to achieve ODA designation by November 2009. The FAA may issue an ODA as needed to any organization with sufficient facilities, resources, personnel, experience with FAA requirements and procedures, and experience to perform the functions. The organization is named ODA Holder, and one or more specific units of suitably trained and experienced personnel within the organization can perform delegated work. For the genesis of ODA see tinyurl.com/2o97fq

Aircraft: AD 2008-01-05  A310
Effect: AD requires further modification by installing an additional protection
sleeve and segregating route 2S in the RH pylon area. This AD results from
analysis of wire routing that revealed that route 2S of the fuel electrical
circuit, located in the RH wing, does not provide adequate separation of fuel
quantity indication wires from wires carrying 115-volt alternating current (AC).
AD is to ensure that fuel quantity indication wires are properly separated from
wires carrying 115-volt AC. Improper separation of such wires, in the event of
wire damage, could lead to a short circuit and a possible ignition source, which
could result in a fire in the airplane. Final rule eff 20 Feb

Aircraft: AD 2007-26-21  EMB120
Effect: Icing tunnel tests on an EMB-120 wing section, conducted under a joint
Embraer-NASA (National Aeronautics and Space Administration)--FAA-CTA (Centro
T[eacute]cnico Aeroespacial) research program well after the EMB-120() was type-
certificated, have shown that stick-shaker to stick-pusher speed margins may
drop below the minimum required by the applicable regulations in certain icing
conditions. Although flight tests have shown that the aircraft handling
qualities are not adversely affected, these reduced speed margins may
significantly increase crew workload in certain flight phases. The unsafe
condition is reduced ability of the flightcrew to maintain the safe flight and
landing of the airplane. Final rule eff 20 Feb

Aircraft: AD 2008-02-01  EMB135BJ
Effect: It has been found that some adhesive tapes used in the interior
furnishings do not comply with the applicable flammability requirements. In case
of some nearby ignition source, fire may propagate to the aircraft. AD is to
require actions to correct the unsafe condition on these products. Final rule
eff 20 Feb

Aircraft: AD 2008-02-02  ERJ170 / ERJ190
Effect: It has been found that the implementation of the Inertial Reference
Units (IRU) on the ERJ-170 [and ERJ-190] may lead, in certain degraded modes, to
an erroneous Flight Path Angle (FPA) indication on both Primary Flight Displays,
with no alert to the flight crew. On the ERJ-170 [and ERJ-190], FPA is
considered as important as pitch and bank angle for piloting purposes. The
unsafe condition is reduced ability of the flightcrew to control the flight path
of the airplane. Final rule eff 20 Feb

Aircraft: AD 2008-02-03  Pilatus PC-12
Effect: It has been found that some of the above mentioned MLG special bolts can
be defective. The problem is only applicable to specific bolts with serial
numbers that start with the letters AT or have the supplier code AT.
Investigations revealed that there is a possibility for hydrogen embrittlement
which occurs during the manufacture process. Components in this condition can
decrease the specific fatigue life and could lead to MLG collapse during
operation with consequent loss of airplane control. Final rule eff 20 Feb

Aircraft: 2007-NM-249-AD  Airbus Model A318, A319, A320, and A321
Effect: Existing AD currently requires repetitive inspections for cracking in
the forward lug of the support rib 5 fitting of both main landing gear (MLG),
and repair if necessary... and also provides optional terminating actions for
certain airplanes, as well as other optional methods for complying. This
proposed AD would continue to require repetitive inspections for cracking in the
forward lug of the support rib 5 fitting of the left and right MLG at new
repetitive intervals in accordance with new service information, and repair or
replacement of any cracked MLG fitting if necessary....but would also require
modification of the rib bushings of the left and right MLG (which would end the
repetitive inspections). AD results from cracks found in the forward lug of the
MLG support rib 5 fitting. AD is to prevent cracking in the forward lug of the
MLG, which could result in failure of the lug and consequent collapse of the MLG
during takeoff or landing. NPRM comment by 13 Feb 08

Aircraft: 2007-NM-230-AD 727-200 Equipped With an Auxiliary Fuel Tank System per
STC SA1350NM
Effect: AD results from fuel tank system reviews conducted by the manufacturer
that identified potential unsafe conditions for which the manufacturer has not
provided corrective actions. AD is to prevent the potential of ignition sources
inside fuel tanks, which, in combination with flammable fuel vapors, could
result in fuel tank explosions and consequent loss of the airplane. NPRM comment
by 28 Feb 08

Aircraft: 2007-NM-203-AD Boeing 757 2007-NM-204-AD Boeing 767 2007-NM-183-AD
Boeing 777
Effect: Proposed AD would require an inspection to determine the manufacturer
and manufacture date of the oxygen masks in the passenger service units and the
lavatory and attendant box assemblies, and corrective action if necessary.
Proposed AD results from a report that several passenger masks with broken in-
line flow indicators were found following a mask deployment. AD is to prevent
the in-line flow indicators of the passenger oxygen masks from fracturing and
separating, which could inhibit oxygen flow to the masks and consequently result
in exposure of the passengers and cabin attendants to hypoxia following a
depressurization event.  NPRM comment by 28 Feb 08

Aircraft: 2007-NM-328-AD  DC-10 and MD-10
Effect: Proposed AD would require repetitive inspections for the presence of
stray nickel or chrome plating deposits on the air filler valve bore of certain
main landing gear (MLG) shock strut cylinders, and if necessary, related
investigative and corrective actions. Doing the corrective action would
terminate the repetitive inspections. Proposed AD results from a report of a
left MLG collapse during landing rollout. We are proposing this AD to detect and
correct  stray nickel and chrome plating deposits, corrosion, and cracking of
the air filler valve bore on the MLG cylinder, which could result in landing
gear failure, significant damage to the airplane, and injury to personnel. NPRM
comment by 28 Feb 08

Aircraft: AD 2008-01-04  CL-600-2B19
Effect: Bombardier CL-600-2B19 airplanes have had a history of flap failures at
various positions for several years. Flap failure may result in a significant
increase in required landing distances and higher fuel consumption than planned
during a diversion. AD requires actions to correct the unsafe condition on these
airplanes.  Final rule eff 15 Feb

Aircraft: AD 2007-26-11 Intertechnique Zodiac Aircraft Systems,  Oxygen Reserve
Cylinders
Effect: AD is issued following information concerning the risk of high-pressure
oxygen cylinder tearing with sudden emptying. These cylinders are used for
missions at high altitudes or to ensure respiratory air for passengers feeling
sick. It has been demonstrated that the material characteristics of the Aluminum
Alloy 5283 (AA5283) from which the cylinders are manufactured deteriorate in the
course of time and may possibly allow these oxygen cylinders to tear and
abruptly vent aboard an aircraft. This unsafe condition requires immediate
action due to the risk of oxygen cylinders exploding on board an aircraft and
creating a fire hazard. Final rule eff 28 Jan